Michael C Blair

US Patent:

7766615, Aug 3, 2010

Filed:

Feb 21, 2007

Appl. No.:

11/708738

Inventors:

Brandon W. Spangler - Vernon CT, US
Michael F. Blair - Manchester CT, US

Assignee:

United Technlogies Corporation - Hartford CT

International Classification:

F01D 25/12

US Classification:

416 1, 416 97 R

Abstract:

A turbine engine component has an airfoil portion having a pressure side and a suction side, a trailing edge discharge slot, and a suction side lip downstream of an exit of the trailing edge slot. The suction side lip is provided with negative features for increasing local heat transfer coefficient in the region of the suction side lip.

US Patent:

7837441, Nov 23, 2010

Filed:

Feb 16, 2007

Appl. No.:

11/707702

Inventors:

Brandon W. Spangler - Vernon CT, US
Michael F. Blair - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 5/08

US Classification:

416 97R, 415115

Abstract:

Turbine components, and in particular turbine blades, are provided with impingement cooling channels. Air is delivered along central channels, and the central channels deliver the air through crossover holes to core channels adjacent both a pressure wall and a suction wall. The air passing through the crossover holes impacts against a wall of the core channels.

US Patent:

7984607, Jul 26, 2011

Filed:

Sep 6, 2007

Appl. No.:

11/850787

Inventors:

Om P. Sharma - South Windsor CT, US
Michael F. Blair - Manchester CT, US

Assignee:

United Technologies Corp. - Hartford CT

International Classification:

F02K 3/00

US Classification:

60268, 4151995

Abstract:

Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.

US Patent:

8066052, Nov 29, 2011

Filed:

Jun 7, 2007

Appl. No.:

11/759525

Inventors:

Michael F. Blair - Manchester CT, US

Assignee:

United Technologies Corporation - Harford CT

International Classification:

B22C 9/04
B22C 9/10

US Classification:

164 44, 164 45, 164369

Abstract:

A casting includes a wall thickness check feature for measuring thickness of a wall second aside an in-wall cooling passageway. The thickness is determined by observing the existence and/or size of an opening formed by the feature. The casting is cast from a pattern including portions forming the feature. To manufacture the pattern, a pattern-forming die is assembled with a ceramic feedcore and a refractory metal core (RMC). The assembling leaves an inlet portion of the RMC engaged to the ceramic feedcore and leaves an outlet portion of the RMC engaged to the die. A pattern-forming material is molded in the die at least partially over the ceramic feedcore and RMC. The die is disengaged from the pattern-forming material. The assembling engages a stepped projection of the RMC with a mating surface of the die.

US Patent:

8468797, Jun 25, 2013

Filed:

Dec 29, 2011

Appl. No.:

13/339972

Inventors:

Om P. Sharma - South Windsor CT, US
Michael F. Blair - Manchester CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 29/38
F02K 3/00

US Classification:

60268, 60 39162, 4151995

Abstract:

An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a ratio of a number of stages in the low-pressure turbine to a number of stages in the high-pressure turbine is 2.

US Patent:

8516793, Aug 27, 2013

Filed:

Jun 17, 2011

Appl. No.:

13/163304

Inventors:

Om P. Sharma - South Windsor CT, US
Michael F. Blair - Manchester CT, US

Assignee:

United Technologies Corp. - Hartford CT

International Classification:

F01D 1/02

US Classification:

60268, 4151995

Abstract:

Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity are provided. In this regard, a representative turbine stage for a gas turbine engine includes a first set of rotatable blades operative to be positioned downstream of and adjacent to a first set of vanes, a number of blades of the first set of blades being less than a number of vanes of the first set of vanes.

US Patent:

20120174593, Jul 12, 2012

Filed:

Dec 29, 2011

Appl. No.:

13/340019

Inventors:

Om P. Sharma - South Windsor CT, US
Michael F. Blair - Manchester CT, US
Frederick M. Schwarz - Glastonbury CT, US

International Classification:

F02C 3/10

US Classification:

60774, 60791

Abstract:

An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a number of stages in the low pressure turbine is from three to five.

US Patent:

50908669, Feb 25, 1992

Filed:

Aug 27, 1990

Appl. No.:

7/572739

Inventors:

Michael F. Blair - Vernon CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 518

US Classification:

415115

Abstract:

A two part vane (38) comprises a metallic downstream portion (42) and a high temperature leading edge insert (40) disposed between two retaining buttons (46,48) loosely fit into recesses (50) formed in the inner platform (52) and the outer platform. The separation between the leading edge insert (40) and the downstream portion (42) creates two cooling louvers (64,66) for conducting cooling air from an internal cavity (58) through the cooling louvers (64,66) and down the surfaces (54,56) of the downstream portion (42).