Jeffrey M Crutchfield

US Patent:

8281649, Oct 9, 2012

Filed:

Jun 11, 2010

Appl. No.:

12/814130

Inventors:

Jeffrey M Crutchfield - Jupiter FL, US
Daniel O Davies - Palm City FL, US
Ross H Peterson - Palm Beach Gardens FL, US
Mark M Harris - Palm Beach Gardens FL, US
Natalie L Marshall - Jupiter FL, US

Assignee:

Florida Turbine Technologies, Inc. - Jupiter FL

International Classification:

G01M 15/14

US Classification:

7311201

Abstract:

A test rig that reproduces high temperature and high pressure conditions found in a gas turbine engine for testing materials under these conditions. The test rig includes a combustor surrounded by an upper plenum chamber and an exhaust plenum that receives a hot gas stream from the combustor. A transparent channeling vessel guides the hot gas stream from the combustor over a test specimen on which a material to be tested is mounted. The hot gas stream exits the clear channeling vessel and into the exhaust plenum where the stream is cooled by diluting the stream with cooling air. A viewing portal is located in the exhaust plenum so that the material can be observed through the clear vessel.

US Patent:

8087881, Jan 3, 2012

Filed:

Nov 22, 2008

Appl. No.:

12/276324

Inventors:

Jeffrey M Crutchfield - Jupiter FL, US
Metthew T Coffin - Palm Beach Gardens FL, US

Assignee:

Florida Turbine Technologies, Inc. - Jupiter FL

International Classification:

F01D 5/26
G06F 7/48

US Classification:

415119, 703 7

Abstract:

A stator assembly having an inner shroud and an outer shroud with a plurality of airfoils extending between the shrouds, and a vibration damping horn extending from one of the shrouds and aligned with the airfoil, the vibration damping horn having a higher stiffness than the airfoil, and where the vibration damping horn vibrates against a damping spring or within a viscous fluid to dampen the vibration of the stator assembly. The vibration damping horns are thicker than the airfoils to provide for the higher stiffness. The damping spring is enclosed between the shroud and seal to support the spring.

US Patent:

20210395156, Dec 23, 2021

Filed:

May 19, 2021

Appl. No.:

17/324593

Inventors:

- Indianapolis IN, US
Jeffrey Crutchfield - Long Beach CA, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN

International Classification:

C04B 41/50
C04B 37/00
C04B 41/00
C04B 41/86
F02C 7/30

Abstract:

A method to produce a ceramic matrix composite with controlled surface characteristics includes: applying a scrim ply to a surface of a fiber preform, where the fiber preform includes silicon carbide fibers coated with boron nitride; infiltrating the fiber preform and the scrim ply with a slurry, thereby forming an impregnated ply on an impregnated fiber preform; infiltrating the impregnated fiber preform and the impregnated ply with a melt comprising silicon, and then cooling, thereby forming a ceramic matrix composite having a ceramic surface layer thereon, where the ceramic surface layer has a predetermined thickness and is devoid of boron; machining or grit blasting the ceramic surface layer to form an intermediate layer suitable for coating; and depositing an environmental barrier coating on the intermediate layer. Thus, a ceramic matrix composite coated with the environmental barrier coating is formed with the intermediate layer in between.

US Patent:

20210355835, Nov 18, 2021

Filed:

May 18, 2020

Appl. No.:

16/876852

Inventors:

- Indianapolis IN, US
Anthony Razzell - London, GB
Michael J. Whittle - London, GB
Jeffrey Crutchfield - Long Beach CA, US

International Classification:

F01D 9/04
F01D 25/24

Abstract:

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.

US Patent:

20210246081, Aug 12, 2021

Filed:

Feb 12, 2020

Appl. No.:

16/788917

Inventors:

- Indianapolis IN, US
- London, GB
Michael Whittle - Derby, GB
Jeffrey Crutchfield - Long Beach CA, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN
Rolls-Royce plc - London

International Classification:

C04B 41/45
C04B 41/87
C04B 41/50
C04B 41/52

Abstract:

A ceramic matrix composite (CMC) component is provided that includes: a CMC body in which an environmental protection layer is completely embedded within a CMC material of the CMC body, the environmental protection layer comprising a ceramic that has a higher impact and/or environmental resistance than the CMC material. Methods for manufacturing the CMC component are also provided.

US Patent:

20210108531, Apr 15, 2021

Filed:

Oct 9, 2019

Appl. No.:

16/597495

Inventors:

- Indianapolis IN, US
- Cypress CA, US
Jeffrey M. Crutchfield - Long Beach CA, US
Jeffrey A. Walston - Indianapolis IN, US

International Classification:

F01D 11/08
F01D 25/24
F01D 9/04

Abstract:

A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.

US Patent:

20210062824, Mar 4, 2021

Filed:

Sep 23, 2019

Appl. No.:

16/579011

Inventors:

- Indianapolis IN, US
Jeffrey Crutchfield - Indianapolis IN, US
Nate Cooper - Avon IN, US
Mark Whitlock - Zionsville IN, US
Nathan Ottow - Indianapolis IN, US

Assignee:

Rolls-Royce Corporation - Indianapolis IN
Rolls-Royce North American Technologies Inc. - Indianapolis IN

International Classification:

F04D 29/42
F04D 29/16
F01D 5/04
F01D 11/22
F04D 17/02
F04D 17/10
F02C 3/08
F04D 27/02

Abstract:

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

US Patent:

20200378264, Dec 3, 2020

Filed:

May 31, 2019

Appl. No.:

16/428330

Inventors:

- Indianapolis IN, US
Jeffrey M. Crutchfield - Indianapolis IN, US

International Classification:

F01D 5/22
F02C 7/28
F02C 7/24
F01D 25/00

Abstract:

A turbine shroud assembly of a gas turbine engine includes seal segments made from ceramic matrix composite materials. The mounting assembly used to support the seal segments has heat shields adapted to resist radiant heating from the seal segments, especially portions of the seal adjacent to a primary gas path along the turbine shroud assembly.