JOHN DAVID MEMMER
Pilots at Bartles Ct, Simpsonville, SC
License number
South Carolina A3818454
Issued Date
Oct 2016
Expiration Date
Oct 2018
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
2 Bartles Ct, Simpsonville, SC 29681
Professional information
Gas Turbomachine Including A Counter-Flow Cooling System And Method
US Patent:
2013029, Nov 7, 2013
Filed:
May 1, 2012
Appl. No.:
13/461035
Inventors:
Kenneth Damon Black - Travelers Rest SC, US
John David Memmer - Simpsonville SC, US
John David Memmer - Simpsonville SC, US
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F04D 31/00
US Classification:
415 1, 415116
Abstract:
A gas turbomachine includes a casing assembly surrounding a portion of the gas turbomachine and a counter-flow cooling system arranged within the casing. The counter-flow cooling system is configured and disposed to guide cooling fluid through the casing assembly in a first axial direction and return cooling fluid through the casing assembly in a second axial direction that is opposite the first axial direction.
Compressor Stator Floating Tip Shroud And Related Method
US Patent:
2006004, Mar 2, 2006
Filed:
Aug 30, 2004
Appl. No.:
10/928735
Inventors:
Nicholas Martin - Simpsonville SC, US
John Memmer - Simpsonville SC, US
Ronald Denmark - Greenville SC, US
John Memmer - Simpsonville SC, US
Ronald Denmark - Greenville SC, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 5/30
US Classification:
41621900R
Abstract:
A stator blade segment for a compressor includes an inner ring segment and an outer ring segment and a plurality of stator blades extending radially between the inner and outer ring segments, the stator blade secured to the outer ring at a shank portion of the blade and loosely held in a slot in the inner ring segment at a tip portion of the blade, the slot formed to substantially match a cross-sectional profile of the tip portion of the blade but sized to create a clearance between the tip portion and the slot.
Patch Ring Segment For A Turbomachine Compressor
US Patent:
2011029, Dec 8, 2011
Filed:
Jun 3, 2010
Appl. No.:
12/793191
Inventors:
John David Memmer - Simpsonville SC, US
Jeffrey Craig Moree - Greer SC, US
Jeffrey Craig Moree - Greer SC, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 11/08, B23P 6/00
US Classification:
4151734, 29888021
Abstract:
A turbomachine includes a compressor provided with a casing having an inner surface defining a flow path. At least one blade is rotatable within the flow path. The at least one blade includes a tip portion that is spaced from the inner surface. At least one patch ring segment is mounted to the inner surface of the casing. The at least one patch ring segment includes a body having a first end that extends to a second end through a surface portion. A first wall member extends from the first end and a second wall member extends from the second end. The first and second wall members include in-turned sections that define a C-shaped cross-section of the at least one patch ring segment.
Heating System For Use In A Turbine Engine And Method Of Operating Same
US Patent:
2012029, Nov 29, 2012
Filed:
May 24, 2011
Appl. No.:
13/114752
Inventors:
Maruthi Prasad Manchikanti - Bestawaripeta, IN
John David Memmer - Simpsonville SC, US
John David Memmer - Simpsonville SC, US
International Classification:
F02C 1/00, F01D 5/08
US Classification:
60772, 415177
Abstract:
A method of operating a turbine engine including coupling a heating assembly to the turbine engine for selectively heating a compressor casing. A sensor transmits a first monitoring signal indicative of a speed of a rotor assembly to a controller. The controller determines whether the turbine engine is operating in a first operating mode based at least in part on the received first monitoring signal, wherein during the first operating mode a minimum clearance distance is defined between the rotor assembly and the compressor casing. The compressor casing of the turbine engine is heated to increase the clearance distance between the compressor casing and the rotor assembly, if the turbine engine is in the first operating mode.
In-Situ Gas Turbine Rotor Blade And Casing Clearance Control
US Patent:
2013023, Sep 12, 2013
Filed:
Mar 12, 2012
Appl. No.:
13/417345
Inventors:
Charles Alexander Smith - Greenville SC, US
John David Memmer - Simpsonville SC, US
Tushar Sharadchandra Desai - Greer SC, US
John David Memmer - Simpsonville SC, US
Tushar Sharadchandra Desai - Greer SC, US
International Classification:
F01D 9/04, F01D 1/04
US Classification:
415200
Abstract:
A method and system for protecting the rotor blade tips of rotary machines, particularly the compressors of gas turbine engines, comprising a rotor assembly having a plurality of circumferentially spaced-apart rotor blades, with each blade extending radially outwardly from an inner wheel disk; a stator assembly comprising one or more rows of spaced-apart vanes extending between adjacent rows of the rotor blades; a casing extending circumferentially around the rotor and stator assemblies; and an abradable ceramic coating applied to selected areas of the interior cylindrical surface of the rotor casing to thereby provide a minimum clearance between the casing and rotor blades during start up and to thereafter ensure an effective compressor seal for compressed gas flow.