University of Virginia Patent Foundation

University of Illinois

Rolls-royce North American Technologies Inc.

Other

Eric Loth

Michael S Selig

Philip Harold Snyder

Dominic L Barone

Scott R White

John Lodewyk Loth

Crawford F Smith, Iii

Andrew Alleyne

Jagdish S Sokhey

Daniel Tortorelli

Philippe H Geubelle

J Craig Dutton

Sang Hak Lee

Holger Babinsky

Adam Steele

David Davis

Stephen T Mcllwain

Francis Loth

Brian J Connolly

Yong Han Yeong

Athanasios Milionis

Dominic Louis Barone

An inlet duct for a gas turbine engine includes a particle separator, a scavenge duct, and a layer of material having a low coefficient of restitution. The particle separator including an outer wall spaced, an inner wall, and a splitter located radially between the outer wall and the inner wall. The scavenge duct is coupled with particle separator. The layer of material is located on at least one of the outer wall, the splitter, and the scavenge duct.

Turbine engine inertial particle separator with particle rebound suppression

A downwind morphing rotor that exhibits bending loads that will be reduced by aligning the rotor blades with the composite forces. This reduces the net loads on the blades which therefore allow for a reduced blade mass for a given maximum stress. The downwind morphing varies the amount of downstream deflection as a function of wind speed, where the rotor blades are generally fully-aligned to non-azimuthal forces for wind speeds between rated and cut-out conditions, while only the outer segments of the blades are generally aligned between cut-in and rated wind speeds. This alignment for large (MW-scale) rated turbines results in much larger downstream deflections of the blades at high wind speeds as compared to that of a conventional rigid single-piece upwind turbine blade.

Morphing segmented wind turbine and related method

An air-inlet duct includes an outer wall, an inner wall, and a splitter. The splitter cooperates with the outer wall to establish a particle separator which separates particles entrained in an inlet flow moving through the air-inlet duct to provide a clean flow of air to a compressor section of a gas turbine engine.

Particle separator

A wind turbine for generating electricity having a turbine assembly mounted on an inner support positioned within an aerodynamic fairing. The turbine assembly has an electrical generator positioned on the inner support and having a rotor shaft rotatable by a rotor blade. The aerodynamic fairing reduces the drag and wake created by the inner support.

2-D fairing for a wind turbine tower

A downwind morphing rotor that exhibits bending loads that will be reduced by aligning the rotor blades with the composite forces. This reduces the net loads on the blades which therefore allow for a reduced blade mass for a given maximum stress. Also provided is a pre-aligned configuration rotor whereby the rotor geometry and orientation does not change with wind speed, and instead is fixed at a constant downwind deflection consistent with alignment at or near the rated wind speed conditions. Also provided is a twist morphing rotor where the airfoil-shapes around the spars twist relative to the wind due to aerodynamic forces so as to unload the rotors when there is a gust. This can help reduce unsteady stresses on the blade and therefore may allow for reduced blade mass and cost. The twist morphing rotor may be combined with either downwind morphing rotor or pre-alignment rotor.

Devices for generating streamwise vorticity in a boundary includes various forms of vortex generators. One form of a split-ramp vortex generator includes a first ramp element and a second ramp element with front ends and back ends, ramp surfaces extending between the front ends and the back ends, and vertical surfaces extending between the front ends and the back ends adjacent the ramp surfaces. A flow channel is between the first ramp element and the second ramp element. The back ends of the ramp elements have a height greater than a height of the front ends, and the front ends of the ramp elements have a width greater than a width of the back ends.

Vortex generators to control boundary layer interactions

Apparatus for controlling shock/boundary-layer interactions created by a supersonic shock on a surface of a structure, includes a cavity formed in the structure and having an opening on the surface. A plate is attached to the surface and covers the opening. A plurality of flaps are formed on the plate and is operable to cooperatively close the opening in response to subsonic airflow condition over the flaps, and open the opening to permit airflow through the cavity in response to supersonic airflow conditions over the flaps.

Method and apparatus for control of shock/boundary-layer interactions

A passive transpiration system for controlling interaction between turbulent boundary layer air and an impinging shock during supersonic airflow by application of a panel including passively activated mesoflaps that direct air circulation through a cavity in response to supersonic airflow. The mesoscopic flaps are preferably arranged in a matrix on one side of a cavity. The flaps deflect to allow air to circulate through the cavity during supersonic airflow, thus controlling the interaction between boundary layer air and air from the impinging shockwave. The flaps open to varying degrees depending on the speed of the airflow. The preferred structure includes channel sidewalls arranged parallel to one another and open on one end, creating multiple cavities. The sidewalls are connected by struts. Rows of flap support beams are connected to the sidewalls. The flaps are connected on one end to the beams, enabling them to deflect over their remainder in response to aerodynamic pressures. This structure enables the flaps to open air pathways into the cavity in response to supersonic airflow and to close the cavity to airflow in response to subsonic conditions without a priori knowledge of the precise spanwise and streamwise location of the shockwave.

Mesoflap passive transpiration system and method for shock/boundary

The 'Isolated Combustion and Dilution Expansion (ICADE) Engine', is a piston/cylinder arrangement used primarily for the compression of air and the expansion of diluted hot combustion products. Fuel injection and rapid combustion take place inside a separate combustion chamber, using a near stoichiometric mixture. The combustion pressurization provides the pressure needed to accelerate the combustion products tangentially into the donut shaped cavity formed by the piston/cylinder clearance. There they establish a vortex which enhances rapid mixing, rapid cooling to quench NO.sub.x forming reactions and to temporarily store the kinetic energy of the combustion products to limit the combustion pressure peak acting on the piston surface. The tangential entry also permits detonation combustion without normal shock reflections on the piston surface, thus preventing 'knock'. Only during the compression stroke, is the combustion chamber isolated from the piston/cylinder arrangement, by a valve with 'controlled leakage'. During the compression stroke, this 'leaky valve' keeps the combustion chamber pressure lower than the pressure inside the cylinder. This controlled pressure difference serves to: prevent fuel from escaping into the cylinder, produce good fuel mixing with combustion air, permits the use of low octane fuel at moderate compression ratio inside the combustor, while the cylinder operates at high compression ratio for high thermal efficiency. Power level control is obtained by modulating the 'leaky valve' to regulate the supply of combustion air, fuel flow control is separate. This configuration eliminates the need for a cylinder intake throttle valve.

Growing community of inventors

Charlottesville, VA, United States of America

Eric Loth