Gorazd Medic

20080015825, Jan 17, 2008

Jul 11, 2006

11/484985

Georgi Kalitzin - Stanford CA, US
Gorazd Medic - San Francisco CA, US
Jeremy Alan Templeton - Oakland CA, US

G06F 17/10

703 2

A technique that improves large-eddy simulation consists in replacing the instantaneous sub-grid scale eddy-viscosity (such as the dynamic Smagorinsky model eddy-viscosity) in the near-wall region with an eddy-viscosity computed from Reynolds Averaged Navier-Stokes eddy-viscosity and corrected dynamically using the resolved turbulent stress. The near-wall eddy-viscosity formulation is applied either with a wall stress model on coarse grids that do not resolve the wall or with wall-resolved grids coarsened in the wall-parallel directions. Reynolds averaged Navier-Stokes eddy-viscosity is computed either from a look-up table or from a simultaneous solution of a Reynolds Averaged Navier-Stokes turbulence model.

20210003030, Jan 7, 2021

Jul 2, 2019

16/460060

- Farmington CT, US
Zaffir A. Chaudhry - South Glastonbury CT, US
Simon W. Evans - Farmington CT, US
Gorazd Medic - West Hartford CT, US
Dilip Prasad - North Granby CT, US

F01D 17/16
F01D 17/24
F01D 9/04

A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.

20200332673, Oct 22, 2020

Apr 18, 2019

16/388199

- Farmington CT, US
Andrzej Ernest Kuczek - Bristol CT, US
Zaffir A. Chaudhry - Glastonbury CT, US
Gorazd Medic - West Hartford CT, US
Dilip Prasad - North Granby CT, US

F01D 11/22
F01D 9/04

A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.

20200325790, Oct 15, 2020

Apr 15, 2019

16/384076

- Farmington CT, US
Simon W. Evans - Farmington CT, US
Dilip Prasad - North Granby CT, US
Gorazd Medic - West Hartford CT, US
Georgi Kalitzin - West Hartford CT, US
Dmytro Mykolayovych Voytovych - Rocky Hill CT, US

F01D 11/10
F02C 7/28

A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.

20200318549, Oct 8, 2020

Apr 4, 2019

16/375018

- Farmington CT, US
Gorazd Medic - West Hartford CT, US
Om P. Sharma - South Windsor CT, US
Timothy S. Snyder - Glastonbury CT, US

F02C 7/232
F02C 3/06
F02C 3/14
F02C 7/24

A combustor for use in a gas turbine engine including: a radially inward heat shield panel; and a radially outward heat shield panel located radially outward of the radially inward heat shield panel, the radially inward heat shield panel and the radially outward heat shield panel being in a facing spaced relationship defining a combustion chamber therebetween, wherein at least one of the radially inward heat shield panel and the radially outward heat shield panel has a non-axisymmetric shape.

20200248575, Aug 6, 2020

Feb 6, 2019

16/268683

- Farmington CT, US
Gorazd Medic - West Hartford CT, US
Om P. Sharma - South Windsor CT, US
Junsok Yi - South Glastonbury CT, US
Dilip Prasad - North Granby CT, US

F01D 11/00

A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.

20190186501, Jun 20, 2019

Dec 19, 2017

15/847371

- Farmington CT, US
Gorazd Medic - West Hartford CT, US

United Technologies Corporation - Farmington CT

F04D 29/56
F01D 17/16
F01D 5/14

An inlet guide vane is disclosed. The inlet guide vane includes a strut and a flap having a radial length in a radial direction. The flap includes a radially inner portion having a first angular orientation with respect to the strut, a radially outer portion having a second angular orientation with respect to the strut, and a transition portion intermediate the radially inner portion and the radially outer portion, wherein the first angular orientation transitions to the second angular orientation along a portion of the radial length.