Atul G Kohli

7845907, Dec 7, 2010

Jul 23, 2007

11/781499

Edward F. Pietraszkiewicz - Southington CT, US
Atul Kohli - Tolland CT, US

United Technologies Corporation - Hartford CT

F01D 5/18

416 97R

A blade for a turbine engine includes structure providing spaced apart suction and pressure sides. A cooling passage includes a first passageway near the pressure side and a second passageway in fluid communication with the first passageway. The second passageway is arranged between the first passageway and the suction side. The cooling passage provides a serpentine cooling path that is arranged in a direction transverse from a chord extending between trailing and leading edges of the blade. During use, cooling fluid is supplied to the pressure side through first cooling apertures fluidly connected to the first passageway to the suction side through second cooling apertures fluidly connected to the other passage way. The first passageway is at a higher pressure that then second passageway so that cooling fluid is provided by the cooling passage to the pressure and suction sides in a balanced fashion.

7883320, Feb 8, 2011

Jan 24, 2005

11/041791

Edward F. Pietraszkiewicz - Southington CT, US
Kevin J. Klinefelter - Uncasville CT, US
Atul Kohli - Tolland CT, US
Todd R. Coons - Gilbert AZ, US

United Technologies Corporation - Hartford CT

F01D 5/08

416 97R

The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased.

7980819, Jul 19, 2011

Mar 14, 2007

11/685840

Jason Edward Albert - West Hartford CT, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US

United Technologies Corporation - Hartford CT

F01D 5/18

416 97R, 416 96 R

An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.

8105030, Jan 31, 2012

Aug 14, 2008

12/191572

William Abdel-Messeh - Middletown CT, US
Michael F. Blair - Manchester CT, US
Atul Kohli - Tolland CT, US
Justin D. Piggush - Hartford CT, US

United Technologies Corporation - Hartford CT

F01D 5/08
F01D 5/18
F01D 5/14
F04D 29/58

416 95, 416231 R, 416232, 415115

Cooled airfoils and gas turbine engine systems involving such airfoils are provided. In this regard, a representative cooled airfoil includes: an exterior surface defining a leading edge, a trailing edge, a suction side and a pressure side; an interior surface defining an interior cavity; trenches in the exterior surface oriented spanwise along the leading edge; and cooling holes communicating between the interior cavity and the trenches such that cooling air provided to the interior cavity flows from the interior cavity though the cooling holes into the trenches, the cooling holes having exterior apertures located in the trenches and interior apertures located at the interior surface.

20110132876, Jun 9, 2011

Jan 12, 2011

13/005304

Edward F. Pietraszkiewicz - Southington CT, US
Kevin J. Klinefelter - Uncasville CT, US
Atul Kohli - Tolland CT, US
Todd R. Coons - Gilbert AZ, US

United Technologies Corporation - Hartford CT

B26F 1/28
B23H 1/00

219 6917, 83 30

The diffusion opening in the cooling hole of an airfoil is formed by an EDM process in which the outwardly flaring sidewalls of the opening, rather then having surfaces that are approximated to be smooth by having many small ribs formed therein, are formed with a relatively few ribs with both longitudinally extending and radially extending surfaces that are substantially greater in dimension than those as normally formed. In this manner, the machining process is simplified and expedited, while at the same time, the cooling efficiency is increased.

20120027619, Feb 2, 2012

Jun 14, 2011

13/159469

Jason Edward Albert - West Hartford CT, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US

F01D 5/00
B23P 15/02
F01D 25/00

416248, 29889721

An airfoil for a turbine engine includes a structure having a cooling passage that has a generally radially extending cooling passageway arranged interiorly relative to an exterior surface of the structure. The cooling passageway includes multiple cooling slots extending there from toward the exterior surface and interconnected by a radially extending trench. The trench breaks the exterior surface, and the exterior surface provides the lateral walls of the trench. The airfoil is manufactured by providing a core having multiple generally axially extending tabs and a generally radially extending ligament interconnecting the tabs. The structure is formed about the core to provide the airfoil with its exterior surface. The ligament breaks the exterior surface to form the radially extending trench in the exterior surface of the structure.

20180340426, Nov 29, 2018

May 25, 2017

15/605458

- Farmington CT, US
Wolfgang Balzer - Wethersfield CT, US
Atul Kohli - Tolland CT, US

F01D 5/18
F02C 3/04

In one embodiment, a component for a gas turbine engine is provided. The component including: an airfoil having a tip portion; a tip shelf located in the tip portion; a first plurality of cooling openings located in an edge of the tip shelf that extends along at least a portion of a pressure side of the airfoil; and a second plurality of cooling openings located in an edge of the tip portion proximate to the tip shelf that extends along at least a portion of a pressure side of the tip portion.

20180073369, Mar 15, 2018

Sep 15, 2016

15/266855

- Farmington CT, US
Dominic J. Mongillo - West Hartford CT, US
Atul Kohli - Tolland CT, US

F01D 5/18
F01D 25/12
F04D 29/58

An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges to provide an exterior airfoil surface. The pressure and suction side walls are spaced apart from one another in a thickness direction. A stagnation line is located near the leading edge. A cooling passage is provided between the pressure and suction side walls. The showerhead cooling holes are arranged at least one of adjacent to or on the stagnation line. At least one of the showerhead cooling holes has a metering hole fluidly connecting the cooling passage to a diffuser arranged at the exterior airfoil surface. At least one showerhead cooling hole is arranged on each of opposing sides of the stagnation line. Each showerhead cooling hole has the diffuser with a first diffuser angle that expands downstream in the thickness direction in opposing directions from one another when separated by the stagnation line.