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Craig E Heathco

from Avon, IN
Age ~71
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Also known as:
Craig Edward Heathco, Craig F Heathco
Phone and address:
488 Cobblestone Pl, Avon, IN 46123
Related to:
Jennifer Clark, 53Ryan OErin Manson, 35Chad Heathco, 32
Connected to:
Alvin Heathcock, 77Amy J Heathcock, 41Breana L Heathco, 39Brittany Heathcock, 40David M Heathcoat, 63David E Heathcock, 56Dickie L Heathcott, 66Elizabeth T Heathcote, 74Emily L Heathcock, 43Freddy W Heathcock, 43

Craig Heathco Phones & Addresses

  • 488 Cobblestone Pl, Avon, IN 46123
  • Nineveh, IN
  • Greenwood, IN
  • 1816 Foxcliff Est, Martinsville, IN 46151
  • Indianapolis, IN
  • 4096 Brockton Manor North Dr, Greenwood, IN 46143

Work

Company: Rolls royce north america 2007 Position: Senior staff engineer

Education

Degree: BS School / High School: General Motors Institute 1971 to 1976 Specialities: Mechanical Engineering

Skills

Aerospace • Maritime • Power Systems • Aeronautics • Aviation • Systems Engineering • Simulations • Energy • Aerospace Engineering • Helicopters • Engineering • Manufacturing • Program Management • Mechanical Engineering • Gas Turbines • Motors • Engineering Management • Mobile Devices

Languages

English • French

Industries

Airlines/Aviation

Resumes

Resumes

Craig Heathco Photo 1

Craig Heathco

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Location:
488 Cobblestone Pl, Avon, IN 46123
Industry:
Airlines/Aviation
Work:
Rolls Royce North America since 2007
Senior Staff Engineer
Rolls-Royce North America 2004 - 2007
Chief Engineer, High Mach Engines
Rolls-Royce North America 2002 - 2005
Chief Design Engineer Helicopters and Small Gas Turbines
Rolls-Royce North America 1998 - 2002
Engineering Director, Energy and Marine
Rolls-Royce North America 1993 - 1998
Chief Engineer Allison Mobile Power Systems
Education:
General Motors Institute 1971 - 1976
BS, Mechanical Engineering
Skills:
Aerospace
Maritime
Power Systems
Aeronautics
Aviation
Systems Engineering
Simulations
Energy
Aerospace Engineering
Helicopters
Engineering
Manufacturing
Program Management
Mechanical Engineering
Gas Turbines
Motors
Engineering Management
Mobile Devices
Languages:
English
French

Publications

Us Patents

Thrust Balance Of Rotor Using Fuel

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US Patent:
8186168, May 29, 2012
Filed:
Jul 18, 2008
Appl. No.:
12/175705
Inventors:
Craig Heathco - Martinsville IN, US
Assignee:
Rolls-Royce Corporation - Indianapolis IN
International Classification:
F02C 1/00
F02G 3/00
US Classification:
60772, 60734, 60 39091
Abstract:
A method of at least partially balancing axial thrust loads and an engine in which the method is carried out is disclosed herein. The engine includes a combustion chamber and a fuel system operable to direct pressurized fuel to the combustion chamber. The engine also includes a rotor operable to rotate about a centerline axis and subjected to axial thrust loads during operation. The engine also includes a balance piston engaged with the rotor. The balance piston includes a pressure face positioned in a thrust cavity. The engine also includes a fluid passageway extending between the fuel system and the thrust cavity. Pressurized fuel is delivered to the pressure face to counteract axial thrust loads on the rotor.

Power Augmentation System For An Engine Powered Air Vehicle

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US Patent:
20110154805, Jun 30, 2011
Filed:
Dec 21, 2010
Appl. No.:
12/974976
Inventors:
Craig Heathco - Martinsville IN, US
Robert T. Duge - Carmel IN, US
Steven Arlen Klusman - Indianapolis IN, US
International Classification:
F02C 6/14
F02K 3/00
US Classification:
602261, 60793
Abstract:
One embodiment of the present invention is a unique augmented gas turbine engine propulsion system. Another embodiment is a gas turbine engine power augmentation system. Yet another embodiment is a system for augmenting power in an engine powered air vehicle. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Turbine Based Combined Cycle Engine

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US Patent:
20120159925, Jun 28, 2012
Filed:
Dec 27, 2010
Appl. No.:
12/978876
Inventors:
Robert T. Duge - Carmel IN, US
Craig Heathco - Martinsville IN, US
Brian Paul King - Greenwood IN, US
International Classification:
F02K 3/06
US Classification:
60204, 602263
Abstract:
An aircraft powerplant is disclosed that can be operated in at least three modes including as a gas turbine engine, as an engine having a ramburner, and as an engine having a forward compression combustor engine such as a ramjet and/or scramjet. An airflow valve is provided to direct air to a downstream portion of the aircraft engine and can be positioned as a function of the aircraft operating modes. The valve can be used to cocoon the gas turbine engine.

Variable Cycle Gas Turbine Engine

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US Patent:
20120233980, Sep 20, 2012
Filed:
Dec 27, 2011
Appl. No.:
13/337924
Inventors:
Craig Heathco - Martinsville IN, US
International Classification:
F02K 3/04
F02C 3/04
US Classification:
602261, 60 3915
Abstract:
One embodiment of the present invention is a unique variable cycle gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for variable cycle gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Inlet Particle Separator With Anti-Icing Means

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US Patent:
48605344, Aug 29, 1989
Filed:
Aug 24, 1988
Appl. No.:
7/235586
Inventors:
Sydney E. Easley - Indianapolis IN
Craig E. Heathco - Indianapolis IN
Clayton L. Smith - Brownsburg IN
Assignee:
General Motors Corporation - Detroit MI
International Classification:
F02G 300
US Classification:
60 39092
Abstract:
A gas turbine engine inertial inlet particle separator having anti-icing. The separator has inner and outer walls defining a main inlet channel and splitter walls dividing the main channel into inner and outer branches. At least one of the walls has a surface portion subject to icing and a partition on the separator is closely disposed behind the one wall to define therewith a narrow annular tunnel. An inlet passage ducts hot compressed air from the engine to one end of the narrow tunnel and a discharge passage ducts the hot compressed air from the other end of the tunnel to a discharge, the flow area of the tunnel being less than the flow area of at least one of the discarge and inlet passages so that the tunnel defines a high velocity, enhanced heat transfer segment of a heating air channel consisting of the tunnel and the inlet and discharge passages. Heat conducting bridges extend across the tunnel to further enhance heat transfer to the icing surface portion.

Gas Turbine Engine Heat Exchanger System

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US Patent:
20140356125, Dec 4, 2014
Filed:
Dec 12, 2013
Appl. No.:
14/104299
Inventors:
- Indianapolis IN, US
Daniel J. Vonderwell - Thorntown IN, US
Craig Heathco - Greenwood IN, US
Assignee:
Rolls-Royce North American Technologies, Inc. - Indianapolis IN
International Classification:
F02C 7/05
F02C 7/12
US Classification:
415 1, 4151212
Abstract:
An apparatus includes a gas turbine engine and a heat transfer system. The gas turbine engine includes an inlet particle separator that separates inlet air into scavenge air and clean air. A scavenge air path conveys the scavenge air from the inlet particle separator to the heat transfer system. A heat exchange fluid path conveys a heat exchange fluid to the heat transfer system and a cooled heat exchange fluid away from the heat transfer system. The heat transfer system is configured to transfer heat from the heat exchange fluid path to the scavenge air path to cool the heat exchange fluid.

Aircraft Power System

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US Patent:
20140248121, Sep 4, 2014
Filed:
Dec 26, 2013
Appl. No.:
14/140959
Inventors:
- Indianapolis IN, US
Craig HEATHCO - Greenwood IN, US
Andrew EIFERT - Indianapolis IN, US
Assignee:
Rolls-Royce Corporation - Indianapolis IN
International Classification:
F02C 7/045
US Classification:
415 1, 415119
Abstract:
A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.
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Craig E Heathco from Avon, IN, age ~71 Get Report