Keith A Santeler

US Patent:

6929054, Aug 16, 2005

Filed:

Dec 19, 2003

Appl. No.:

10/741710

Inventors:

James T. Beals - West Hartford CT, US
Samuel D. Draper - Kohler WI, US
Jose A. Lopes - Glastonbury CT, US
Stephen D. Murray - Marlborough CT, US
Brandon W. Spangler - Rocky Hill CT, US
Michael K. Turkington - Manchester CT, US
Bryan P. Dube - Columbia CT, US
Keith A. Santeler - Middletown CT, US
Jacob A. Snyder - Southington CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C009/10

US Classification:

164369, 164397, 164365

Abstract:

A sacrificial core for forming an interior space of a part includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.

US Patent:

7097424, Aug 29, 2006

Filed:

Feb 3, 2004

Appl. No.:

10/771485

Inventors:

Frank Cunha - Avon CT, US
Keith Santeler - Middletown CT, US
Bret Teller - Meriden CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97R

Abstract:

A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro-circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro-circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal convective efficiency, high film coverage, and high cooling effectiveness.

US Patent:

7097425, Aug 29, 2006

Filed:

Mar 16, 2004

Appl. No.:

10/802260

Inventors:

Frank J. Cunha - Avon CT, US
Keith Santeler - Middletown CT, US
Scott W. Gayman - Manchester CT, US
Eric Couch - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97R, 415115

Abstract:

A turbine airfoil includes a plurality of cooling circuits embedded within the pressure and suction sidewalls and a first and a second flow passage. The first flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the pressure sidewall and the second flow passage feeds the coolant fluid to the cooling circuits that are embedded only within the suction sidewall. A method embodiment of the present comprises placing the inlets of the cooling circuits embedded within the first sidewall in flow communication with only one of the flow passages and placing the inlets of the cooling circuits embedded within the second sidewall in flow communication with at least one of the other flow passages to minimize the difference in sink pressures of the suction and pressure sidewalls to ensure ingestion of the coolant fluid into the inlets of the respective cooling circuits.

US Patent:

7108045, Sep 19, 2006

Filed:

Sep 9, 2004

Appl. No.:

10/937067

Inventors:

John D. Wiedemer - Glastonbury CT, US
Keith A. Santeler - Middletown CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/10

US Classification:

164369

Abstract:

A composite core for an investment casting process, the core including both a ceramic portion and a refractory metal portion, with the refractory metal portion being so disposed as to perform the function of a plurality of such refractory metal elements. In particular, a refractory metal element attached to a trailing edge of a ceramic element extends beyond the plane of a tip end of the ceramic element so as to replace the refractory metal element otherwise extending from the ceramic tip edge. The refractory metal element also extends beyond the space to be occupied by the wax casting, both in the direction of the tip end and the trailing edge such that improved placement and securing of the core is facilitated during the casting process. A further embodiment uses a single refractory metal element that extends into both the airfoil portion and an orthogonal extending platform portion thereof.

US Patent:

7185695, Mar 6, 2007

Filed:

Sep 1, 2005

Appl. No.:

11/219156

Inventors:

Keith A. Santeler - Middletown CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/04

US Classification:

164 44, 164 45, 164516

Abstract:

At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

US Patent:

7255536, Aug 14, 2007

Filed:

May 23, 2005

Appl. No.:

11/134927

Inventors:

Frank J. Cunha - Avon CT, US
Eric Couch - South Windsor CT, US
Keith A. Santeler - Middletown CT, US
Scott W. Gayman - Manchester CT, US
Eric A. Hudson - Harwinton CT, US
Christopher Joe - Wethersfield CT, US
Eric Letizia - East Hartford MI, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/18

US Classification:

416 97R, 416193 A

Abstract:

An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

US Patent:

7258156, Aug 21, 2007

Filed:

Sep 19, 2006

Appl. No.:

11/523960

Inventors:

Keith A. Santeler - Middletown CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22C 9/04

US Classification:

164412, 164 44, 164 45

Abstract:

At least one feed core and at least one wall cooling core are assembled with a number of elements of a die for forming a cooled turbine engine element investment casting pattern. A sacrificial material is molded in the die. The sacrificial material is removed from the die. The removing includes extracting a first of the die elements from a compartment in a second of the die elements before disengaging the second die element from the sacrificial material. The first element includes a compartment receiving an outlet end portion of a first of the wall cooling cores in the assembly and disengages therefrom in the extraction.

US Patent:

7270170, Sep 18, 2007

Filed:

Aug 26, 2004

Appl. No.:

10/926476

Inventors:

James T. Beals - West Hartford CT, US
Samuel D. Draper - Kohler WI, US
Jose A. Lopes - Glastonbury CT, US
Stephen D. Murray - Marlborough CT, US
Brandon W. Spangler - Rocky Hill CT, US
Michael K. Turkington - Manchester CT, US
Bryan P. Dube - Columbia CT, US
Keith A. Santeler - Middletown CT, US
Jacob A. Snyder - Southington CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B22D 29/00

US Classification:

164132, 164369

Abstract:

A sacrificial core is used for forming an interior space of a part and includes a ceramic core element and a first core element including a refractory metal element. The ceramic core element may be molded over the first core element or molded with assembly features permitting assembly with the first core element.