Rolls-Royce Corporation

Rolls-Royce North American Technologies Inc.

Donald W Burns

Daniel Kent Vetters

Kaushik Rajashekara

Robert Zeller

Igor Vaisman

Michael James Armstrong

Rigoberto Jorge Rodriguez

Andrew D Copeland

Steven Gagne

Stanford O Clemens

Thomas E Bastnagel

John R Louie

Alan B Cookerly

Robert J Zeller

Douglas M Roever

A magnetic squeeze film damper system comprises a bearing assembly having an outer race with a first outer surface and a first inner surface and a bearing located along the first inner surface. The system further comprises a squeeze film damper housing having a second outer surface and a second inner surface that is contiguous with the first outer surface. A channel having a forward end and an aft end is defined within the housing along the second inner surface, the channel bordered by the first outer surface. The system further includes a first seal gland located along the forward end of the channel and a second seal gland located along the aft end of the channel. Both seal glands comprise a reservoir for holding a magneto-rheological fluid, the reservoir encased in an elastomer. At least one electromagnet is arranged in close proximity to each of the seal glands.

Magnetic squeeze film damper system for a gas turbine engine

One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

System, propulsion system and vehicle

An apparatus, system, and method for a gas turbine engine may include a sectioned heat exchanger. A heat exchanger may include an inlet manifold configured to receive a working fluid. A plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid. Each of the circuits may have a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve. The heat exchanger may further include an outlet manifold configured to pass the working fluid to an outlet. The heat exchanger may include a first sensor configured to measure of first parameter of the first circuit and a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit. A controller may be configured to selectively isolate at least one of the plurality of circuits based on a pressure difference between the first and second parameters.

Sectioned gas turbine engine driven by sCO2 cycle

Control systems and methods for a propulsion system are disclosed in which the propulsion control system is integrated to intelligently control propulsion and minimize transient effects from the power demands of other subsystems.

Intelligent integrated control system and method

Control systems and methods for an aircraft propulsion system are disclosed in which the propulsion control system is integrated to intelligently control aircraft propulsion and minimize transient effects from the power demands of other aircraft subsystems.

Intelligent integrated propulsion control system and method

A system, which may be a propulsion system or a vehicle having a propulsion system, for example, an air-vehicle, a land vehicle or a marine vehicle, includes a gas turbine engine operative to drive a propulsor. The propulsor may be, for example, a fan/turbofan, a propeller, a turbine, or any rotor system for propelling an aircraft; a system for providing tractive effort for a land vehicle, such as one or more transmissions and wheel/track systems; and/or may be one or more marine propulsive devices, such as shrouded or unshrouded propellers, hydrojets and/or jet-pumps for surface vessels and/or submarines. The system also includes an auxiliary power unit. The auxiliary power unit is coupled to the gas turbine engine, and is operative to supply rotational power to the propulsor and to the impart motion to the vehicle using the propulsor, without starting the gas turbine engine.

A thermal system is disclosed in thermal communication with an electrical device. In one form the thermal system is a refrigeration system. The electrical device can be disposed within the refrigeration system such that a working fluid of the refrigeration system exchanges heat with the electrical device. In one embodiment the refrigeration system includes a container in which the electrical device is disposed. The electrical device can be an electrical motor, but other forms are contemplated. The container can be located anywhere in the thermal system. In one non-limiting embodiment the working fluid of the refrigeration system wets a stator of the motor. A partition can be used to separate the stator from the motor to keep the motor free from working fluid.

Thermal system having electrical device

One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Aircraft, propulsion system, and system for taxiing an aircraft

One embodiment of the present invention is a unique aircraft. Another embodiment is a unique propulsion system for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and aircraft propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Aircraft and propulsion system

A method for analyzing and designing structures with structural aliasing. The concept of structural aliasing applies in one embodiment of the present invention to structural systems which are cyclically symmetric. In analyzing and designing structural systems such as wheel assemblies of gas turbine engines, it is possible to group the discrete components so as to aliasingly couple particular ordered excitations and harmonic families. With structural aliasing, it is possible to couple the ordered excitations and harmonic families such that resonant response of the wheel assembly does not occur within the operating range of the engine, and also to have the resonant vibratory mode excited in such a manner that the drive coupling of the wheel dampens the wheel assembly.

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Avon, IN, United States of America

Donald W Burns