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Roy David Fulayter

from Virginia Beach, VA
Age ~50
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Also known as:
Roy D Fulayter, Ray D Fulayter, Roy Sulayter
Related to:
John E Alderson, 99Douglas FulayterKentra FulayterThelma Middleton
Connected to:
Ray D Fulayter, 82Aubrey L Fulbright, 70Bridgette L Fulbright, 29Carolyn L Fulbright, 88Cody Fulbright, 33Connie S Fulbright, 69Daniel R Fulbright, 43Gary Fulbright, 54Jackson R Fulbright, 34Michael T Fulbright, 49

Roy Fulayter Phones & Addresses

  • Virginia Beach, VA
  • 1129 Red Dunes Run, Avon, IN 46123 (317) 272-7071
  • Indianapolis, IN
  • 901 20Th St, Lafayette, IN 47904 (765) 446-0092
  • 1424 Elizabeth St, Lafayette, IN 47904 (765) 742-8253
  • Blacksburg, VA

Resumes

Resumes

Roy Fulayter Photo 1

Roy Fulayter

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Location:
1129 Red Dunes Run, Avon, IN 46123
Industry:
Aviation & Aerospace
Work:
Carrier Corporation Nov 2018 - May 2019
Refrigeration Systems Engineer
Zunum Aero Aug 2017 - Nov 2018
Lead Propulsion Engineer
Rolls-Royce Jan 2004 - Aug 2017
Senior Installations Aero Engineer
Purdue University Aug 1996 - Dec 2003
Research Assistant
Education:
Purdue University 1996 - 2004
Doctorates, Doctor of Philosophy, Philosophy, Mechanical Engineering Purdue University 1996 - 1999
Master of Science, Masters, Mechanical Engineering Virginia Tech 1994 - 1996
Bachelors, Bachelor of Science, Engineering, Mechanical Engineering Tabernacle Baptist High School Virginia Beach, Va
Skills:
Aerodynamics
Aerospace
Finite Element Analysis
Engineering
Ansys
Stress Analysis
Air Compressors
Cfd
Testing
Multi Disciplinary
Gas Turbines
Matlab
Turbomachinery
Labview
Microsoft Excel
Unigraphics
Propulsion
Languages:
French
Roy Fulayter Photo 2

Mechanical Specialist At Rolls-Royce North America

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Position:
Mechanical Specialist at Rolls-Royce North America
Location:
Indianapolis, Indiana Area
Industry:
Aviation & Aerospace
Work:
Rolls-Royce North America
Mechanical Specialist
Purdue University Aug 1996 - Dec 2003
Research Assistant
Rolls-Royce North America Jun 1999 - Aug 2001
Graduate Intern
URS Consultants Jun 1996 - Aug 1996
intern
Education:
Purdue University 2000 - 2004
PhD, Mechanical Engineering Purdue University 1996 - 1999
MS, Mechanical Engineering Virginia Polytechnic Institute and State University 1994 - 1996
BS, Mechanical Engineering

Publications

Us Patents

Fan Assembly

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US Patent:
8469670, Jun 25, 2013
Filed:
Aug 27, 2009
Appl. No.:
12/549071
Inventors:
Roy David Fulayter - Avon IN, US
Bradley T. Fanton - Plainfield IN, US
Assignee:
Rolls-Royce Corporation - Indianapolis IN
International Classification:
F01D 5/30
US Classification:
416221, 416500
Abstract:
A fan assembly is disclosed herein. The fan assembly includes a fan operable to rotate about an axis. The fan includes a hub and a plurality of blades extending radially from the hub relative to the axis. The fan also includes a reinforcing member positioned adjacent to the fan along the axis. The reinforcing member contacts a predetermined subset of less than all of the plurality of blades.

Method And Apparatus For Enhancing Compressor Performance

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US Patent:
8500399, Aug 6, 2013
Filed:
Apr 25, 2007
Appl. No.:
11/789688
Inventors:
Roy Fulayter - Avon IN, US
Steve Wellborn - Indianapolis IN, US
Assignee:
Rolls-Royce Corporation - Indianapolis IN
International Classification:
F01D 9/02
US Classification:
4151821, 415196, 415914
Abstract:
The present invention provides a non-axisymmetric flow member disposed in a duct of a gas turbine engine. The flow member narrows the area aft of a vane to reduce the cross sectional area through which a wake from the vane traverses.

Fan

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US Patent:
20110076148, Mar 31, 2011
Filed:
Sep 30, 2009
Appl. No.:
12/570612
Inventors:
Roy David FULAYTER - Avon IN, US
James Ong - Carmel IN, US
International Classification:
F01D 5/30
B23P 15/04
US Classification:
416204 R, 29889
Abstract:
A fan is disclosed herein. The fan includes a hub portion operable to rotate about an axis. The hub portion extends along the axis between forward and aft ends. The fan also includes at least one platform operably fixed with the hub portion. The at least one platform at least partially encircles the axis. The fan also includes at least one airfoil extending from the at least one platform radially outward relative to the axis between a base and a tip. The at least one platform terminates at forward and aft circumferential edges spaced from one another along the axis. At least one of the forward and aft circumferential edges extends about the axis and along the axis.

Rotating Structure And A Method Of Producing The Rotating Structure

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US Patent:
20170107999, Apr 20, 2017
Filed:
Oct 19, 2015
Appl. No.:
14/886904
Inventors:
- Indianapolis IN, US
Roy David Fulayter - Avon IN, US
International Classification:
F04D 29/34
F04D 29/32
F04D 29/64
B23P 15/00
Abstract:
According to one aspect, a rotating structure comprises a hub having a mounting slot defined by a cavity surface and a body having an anchor structure disposed in the mounting slot. A wear member is disposed between the anchor structure and the cavity surface and the wear member has at least first and second portions of first and second material characteristics, respectively.

Multi-Stage Co-Rotating Variable Pitch Fan

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US Patent:
20160265547, Sep 15, 2016
Filed:
Mar 9, 2016
Appl. No.:
15/065247
Inventors:
- Indianapolis IN, US
Roy D. Fulayter - Avon IN, US
International Classification:
F04D 29/36
F04D 29/32
Abstract:
A fan for a gas turbine engine is disclosed. The fan includes a fan disk and a plurality of fan blades coupled to the fan disk. The fan disk is adapted for rotation about a central axis. The fan blades are coupled to the fan disk for rotation therewith about the central axis.

Gas Turbine Engine Flow Path Geometry

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US Patent:
20150128604, May 14, 2015
Filed:
Nov 27, 2013
Appl. No.:
14/092356
Inventors:
- Indianapolis IN, US
Roy D. Fulayter - Avon IN, US
Jonathan M. Rivers - Indianapolis IN, US
International Classification:
F04D 19/02
F02C 3/00
F02C 9/16
US Classification:
60772, 415207, 415 1
Abstract:
A flow path surface of a gas turbine engine at the location of a bladed component is disclosed in which the flow path surface includes a cylindrical upstream side and a conical downstream side. The bladed component is located at the intersection of the cylindrical upstream side and the conical downstream side. The cylindrical upstream side can extend from a leading edge of the bladed component, or a point upstream of it, to a location between the leading edge and trailing edge of the component. The conical downstream side can extend past the trailing edge of the bladed component. The bladed component can be a fan blade or a compressor blade.

Ultra High Bypass Ratio Turbofan Engine

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US Patent:
20140363276, Dec 11, 2014
Filed:
Dec 10, 2013
Appl. No.:
14/101438
Inventors:
- Indianapolis IN, US
Roy D. Fulayter - Avon IN, US
Assignee:
Rolls-Royce Corporation - Indianapolis IN
Rolls-Royce North American Technologies, Inc. - Indianapolis IN
International Classification:
F02K 3/075
US Classification:
4151242
Abstract:
An ultra high bypass ratio turbofan engine includes a variable pitch fan, a low pressure turbine, a reduction gearbox, and a plurality of outlet guide vanes. The ultra high bypass ratio turbofan engine has a bypass ratio between about 18 and about 40. The variable pitch fan and the low pressure turbine are coupled together by the reduction gearbox. The reduction gearbox reduces the speed of the variable pitch fan relative to the low pressure turbine. The plurality of outlet guide vanes are spaced aft of the variable pitch fan and are axially swept. The variable pitch fan and the low pressure turbine are configured to generate a fan pressure ratio between about 1.15 and about 1.24.

Turbine Engine And Vane System

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US Patent:
20140314548, Oct 23, 2014
Filed:
Jun 30, 2014
Appl. No.:
14/319702
Inventors:
- Indianapolis IN, US
Roy David Fulayter - Avon IN, US
International Classification:
F01D 17/10
F02K 3/075
US Classification:
415145, 29889
Abstract:
One embodiment of the present invention is a unique vane system. Another embodiment is a unique gas turbine engine. Another embodiment is a unique method for manufacturing a bypass vane stage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane systems for turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
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Roy David Fulayter from Virginia Beach, VA, age ~50 Get Report