Mark A Costa

US Patent:

7296656, Nov 20, 2007

Filed:

Apr 22, 2005

Appl. No.:

11/112946

Inventors:

Scott Sanicki - East Hampton CT, US
Mark W. Costa - Storrs CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B64C 1/40
B64C 1/12
B64C 1/06
B64D 33/02
F02K 1/82

US Classification:

181210, 181214, 244 1 N, 244131, 244132

Abstract:

A fan case assembly includes a noise attenuation layer that is covered by a face sheet. The face sheet includes a first plurality of openings. The noise attenuation layer includes a plurality of individual cells that are in communication with at least one of the first plurality of openings. Noise energy is communicated through the first plurality of openings into the individual cells and dissipated to reduce noise emissions. A seam in the face sheet is covered to protect the underlying noise attenuation layer from damage by a retainer. The retainer is bonded to the face sheet over the seam and includes a second plurality of holes that communicates noise energy through the retainer to the noise attenuation layer. Communication of noise energy through the retainer provides an acoustically active seam that aids in the dissipation of noise energy and thereby reduces the level of sound emitted from the engine.

US Patent:

20120148392, Jun 14, 2012

Filed:

Feb 16, 2012

Appl. No.:

13/397771

Inventors:

Darin S. LUSSIER - Berlin CT, US
Mark W. COSTA - Storrs CT, US
Sreenivasa R. VOLETI - Farmington CT, US
Rajiv A. NAIK - Glastonbury CT, US

International Classification:

F01D 25/24

US Classification:

415200, 4152141

Abstract:

A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.

US Patent:

20130195605, Aug 1, 2013

Filed:

Jan 31, 2012

Appl. No.:

13/362654

Inventors:

Thomas J. Robertson - Glastonbury CT, US
Mark W. Costa - Storrs CT, US
Johan R. Santana - Westerly RI, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 25/26
B29C 65/00
F01D 9/00
B29C 65/02
F01D 11/08
B23P 15/00

US Classification:

415 1, 415134, 4151731, 2988922, 4151821, 156285, 156 60, 156538

Abstract:

A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.

US Patent:

20130336773, Dec 19, 2013

Filed:

Jun 19, 2012

Appl. No.:

13/526627

Inventors:

Thomas J. Robertson - Glastonbury CT, US
Darin S. Lussier - Berlin CT, US
Mark W. Costa - Storrs CT, US

Assignee:

UNITED TECHNOLOGIES CORPORATION - Hartford CT

International Classification:

F01D 25/24
B23P 17/04

US Classification:

415200, 295272

Abstract:

A composite fan case has a generally cylindrical composite shell, at least one band of sacrificial composite material circumscribing an outer surface of the composite shell, and a metallic rail mounted on the band of sacrificial material. Also disclosed is a method of construction the aforementioned case.

US Patent:

20190128136, May 2, 2019

Filed:

Oct 30, 2017

Appl. No.:

15/797178

Inventors:

- Farmington CT, US
Darin S. Lussier - Guilford CT, US
Mark W. Costa - Storrs CT, US

International Classification:

F01D 21/04
B29C 63/34
F01D 25/24
B29C 53/56

Abstract:

A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

US Patent:

20160195411, Jul 7, 2016

Filed:

Oct 21, 2015

Appl. No.:

14/919225

Inventors:

- Farmington CT, US
Eli Warren - Wethersfield CT, US
Corey A. Benoit - Uncasville CT, US
Edward F. Dreger - Burlington CT, US
Erik D. Rice - Lebanon CT, US
Mark W. Costa - Storrs CT, US

International Classification:

G01D 5/241
F04D 29/32
F01D 21/00
F01D 25/24
G01M 15/14
F01D 5/02

Abstract:

A capacitance probe monitors the distance between a blade tip and a fan, compressor or turbine case. The capacitance probe may be attached to a liner, and may travel with the liner as it radially expands due to thermal changes. The capacitance probe may include a circuit board sensor with a metallic plate, and one or more capacitors. The metallic plate may be encapsulated within an insulating material. A plurality of soft leads may be in electrical communication with the circuit board sensor, allowing a lower lead weight, reduced size and increased flexibility. The soft leads may also be embedded in the liner. In this way, the capacitance probe can record more accurate distance measurements and promote a gas turbine engine's continued and efficient operation.

US Patent:

20160177840, Jun 23, 2016

Filed:

Sep 13, 2013

Appl. No.:

14/410487

Inventors:

- Farmington CT, US
Steven Clarkson - Cheshire CT, US
Mark W. Costa - Storrs CT, US

International Classification:

F02C 7/32
F02C 7/20

Abstract:

A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

US Patent:

20150275692, Oct 1, 2015

Filed:

Feb 22, 2013

Appl. No.:

14/432356

Inventors:

- Hartford CT, US
Sreenivasa R. Voleti - Farmington CT, US
Mark W. Costa - Storrs CT, US
Steven Clarkson - Cheshire CT, US

International Classification:

F01D 25/24
F01D 5/14
F01D 25/30
F01D 5/02

Abstract:

A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture.