JASON A ALBERT
Medical Practice at Salem Rd, Hartford, CT
License number
Florida 66940
Issued Date
Jan 17, 1992
Expiration Date
Dec 1, 1992
Category
Health Care
Type
Emergency Medical Technician
Address
Address
14 Salem Rd, Hartford, CT 06118
Professional information
Cast Features For A Turbine Engine Airfoil
US Patent:
2012002, Feb 2, 2012
Filed:
Jun 14, 2011
Appl. No.:
13/159469
Inventors:
Jason Edward Albert - West Hartford CT, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US
International Classification:
F01D 5/00, B23P 15/02, F01D 25/00
US Classification:
416248, 29889721
Abstract:
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.
Turbine Blade Tip Cooling
US Patent:
7413403, Aug 19, 2008
Filed:
Dec 22, 2005
Appl. No.:
11/317394
Inventors:
Francisco J. Cunha - Avon CT, US
Jason E. Albert - West Hartford CT, US
Jason E. Albert - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/08
US Classification:
416 1, 416 97 R, 416 92, 164369, 164397
Abstract:
A turbine engine blade has an attachment root, a platform outboard of the attachment root, and an airfoil extending from the platform. The airfoil has pressure and suction sides extending between leading and trailing edges. An internal cooling passageway network includes at least one inlet in the root and a plurality of outlets along the airfoil. The passageway network includes a leading spanwise cavity fed by a first trunk. A streamwise cavity is inboard of a tip of the airfoil. A spanwise feed cavity feeds the streamwise cavity absent down-pass. A second trunk feeds the spanwise feed cavity.
Airfoil With Large Fillet And Micro-Circuit Cooling
US Patent:
2006008, Apr 20, 2006
Filed:
Oct 18, 2004
Appl. No.:
10/967558
Inventors:
Frank Cunha - Avon CT, US
Jason Albert - West Hartford CT, US
Jason Albert - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
41609700R
Abstract:
A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which partially defines a fillet cavity therebehind, and cooling air is provided to the fillet cavity and is then routed to the outer surface by way film cooling holes. Various design features are provided to enhance the effectiveness of the cooling air being provided to both the fillet cavity and other cavities within the blade.
Impingement Cooling Of Large Fillet Of An Airfoil
US Patent:
7220103, May 22, 2007
Filed:
Oct 18, 2004
Appl. No.:
10/967557
Inventors:
Frank J. Cunha - Avon CT, US
Jason E. Albert - West Hartford CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Jason E. Albert - West Hartford CT, US
Edward F. Pietraszkiewicz - Southington CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R, 416193 A
Abstract:
A gas turbine engine blade has a relatively large fillet to improve the characteristics of the air flow thereover. The fillet has a thin wall which, together with an impingement rib, defines a fillet cavity therebetween, and cooling air is provided to flow through impingement holes in the impingement rib and impinge on the rear surface of the fillet. The impingement holes are elongated in cross sectional shape with their elongations being orient in a direction generally transverse to a radial direction.
Cast Features For A Turbine Engine Airfoil
US Patent:
7980819, Jul 19, 2011
Filed:
Mar 14, 2007
Appl. No.:
11/685840
Inventors:
Jason Edward Albert - West Hartford CT, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US
Atul Kohli - Tolland CT, US
Eric L. Couch - Frederick MD, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 97R, 416 96 R
Abstract:
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.
Microcircuit Cooling And Tip Blowing
US Patent:
7513744, Apr 7, 2009
Filed:
Jul 18, 2006
Appl. No.:
11/489155
Inventors:
Francisco J. Cunha - Avon CT, US
Jason Edward Albert - West Hartford CT, US
Jason Edward Albert - West Hartford CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/18
US Classification:
416 92, 416 97 R
Abstract:
A turbine engine component has an airfoil portion having a pressure side, a suction side, a leading edge, a trailing edge, and a tip. The component further has a first cooling microcircuit embedded in a pressure side wall, a second cooling microcircuit embedded in a suction side wall, and a system for cooling the tip comprising a first tip cooling microcircuit receiving cooling fluid from the first cooling microcircuit and a second tip cooling microcircuit receiving cooling fluid from the second cooling microcircuit.
Rmc-Defined Tip Blowing Slots For Turbine Blades
US Patent:
2008013, Jun 5, 2008
Filed:
Nov 30, 2006
Appl. No.:
11/606598
Inventors:
Jason Edward Albert - West Hartford CT, US
Francisco J. Cunha - Avon CT, US
Jeffrey S. Beattie - West Hartford CT, US
Francisco J. Cunha - Avon CT, US
Jeffrey S. Beattie - West Hartford CT, US
International Classification:
F01D 5/18, F01D 25/12, B22D 15/00, B22D 19/00, B21D 53/78
US Classification:
416 96 R, 416241 B, 164 6, 164159, 2988971
Abstract:
A process for forming an airfoil portion of a turbine engine component, such as a turbine blade, is described. The process comprises the steps of placing a ceramic core having a configuration of a passageway to be formed in the airfoil portion within a mold, attaching a refractory metal core element to the ceramic core to stabilize a tip region of the ceramic core, and casting the airfoil portion.
Airfoil Trailing Edge Cooling
US Patent:
7438527, Oct 21, 2008
Filed:
Apr 22, 2005
Appl. No.:
11/112149
Inventors:
Jason E. Albert - West Hartford CT, US
Frank J. Cunha - Avon CT, US
Frank J. Cunha - Avon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/08
US Classification:
416 97R, 416 90 R
Abstract:
A turbine airfoil includes a span wise extending cavity formed from a ceramic mold and a slot extending from the cooling air cavity to a trailing edge being formed by a refractory metal core. The refractory metal core facilitates the reduction in the size of the slot and also in the reduction in the size of pedestals which pass transversely through the slot to interconnect the pressure side to the suction side of the airfoil. The blade has a cutback feature to expose a back surface on the inner side of the suction side wall with dimples being formed on the back surface so as to enhance heat transfer characteristics thereof. Provision is made for fabricating the dimples by way of a photo etching process.