ROBERT C MANNING
Electrician in Plum Island, MA
License number
Massachusetts 29835
Issued Date
May 27, 1986
Expiration Date
Jul 31, 2019
Type
Journeyman Electrician
Address
Address
Plum Island, MA 01950
Personal information
See more information about ROBERT C MANNING at radaris.comName
Address
Phone
48 Marlboro Rd, Woburn, MA 01801
47 Stone Horse Rd, Osterville, MA 02655
501 Commercial St APT 4C, Provincetown, MA 02657
4 Landau Rd, Plainville, MA 02762
4 Pilgrim Ln, Medfield, MA 02052
Professional information
Methods And Apparatus For Cooling Gas Turbine Engine Nozzle Assemblies
US Patent:
6746209, Jun 8, 2004
Filed:
May 31, 2002
Appl. No.:
10/160548
Inventors:
Thomas Edward DeMarche - Boxford MA
Robert Francis Manning - Newburyport MA
Robert Francis Manning - Newburyport MA
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 906
US Classification:
416 97R
Abstract:
A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity and a cooling circuit are defined within the airfoil, wherein the suction side and the pressure side extend radially between a tip and a root. The method also includes forming a plurality of cooling slots within the airfoil that extend from the cooling circuit towards the airfoil trailing edge, and forming a control vane within the cooling circuit to facilitate maintaining a substantially constant cooling effectiveness within the cooling circuit.
Turbine Blade For Gas Turbine Engine And Method Of Cooling Same
US Patent:
6402471, Jun 11, 2002
Filed:
Nov 3, 2000
Appl. No.:
09/706387
Inventors:
Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 518
US Classification:
416 97R, 416 96 R, 416193 A, 415115
Abstract:
A turbine blade includes a platform having an internal cavity formed therein and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough, and at least one supply passage extends between the internal cooling circuit and the internal platform cavity for diverting coolant to the internal platform cavity. The coolant is expelled from holes located in the forward and aft edges of the platform for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.
Cooled Airfoil For Gas Turbine Engine And Method Of Making The Same
US Patent:
6422819, Jul 23, 2002
Filed:
Dec 9, 1999
Appl. No.:
09/457652
Inventors:
Gene C. F. Tsai - Lexington MA
Sung Tung - Lexington MA
Terence C. Flaherty - Marblehead MA
Robert F. Manning - Newburyport MA
Sung Tung - Lexington MA
Terence C. Flaherty - Marblehead MA
Robert F. Manning - Newburyport MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F01D 508
US Classification:
416 97R, 416235
Abstract:
An airfoil for use in a gas turbine engine includes a pressure side and a suction side joined at a trailing edge wall that defines a trailing edge. The airfoil includes at least one cooling hole extending through the trailing edge wall so as to pass cooling fluid from the pressure side of the airfoil to the suction side.
Turbine Blade For Gas Turbine Engine And Method Of Cooling Same
US Patent:
6416284, Jul 9, 2002
Filed:
Nov 3, 2000
Appl. No.:
09/706403
Inventors:
Daniel Edward Demers - Ipswich MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA
Robert Francis Manning - Newburyport MA
Paul Joseph Acquaviva - Newburyport MA
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 518
US Classification:
416 97R, 416 96 R, 416193 A, 415115
Abstract:
A turbine blade includes a platform and an airfoil extending radially from the platform. An internal cooling circuit is formed in the airfoil for circulating a coolant therethrough to cool the airfoil. At least one supply passage is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform for cooling the platform.
Turbine Blade Having Opposing Wall Turbulators
US Patent:
5700132, Dec 23, 1997
Filed:
Dec 17, 1991
Appl. No.:
7/809604
Inventors:
Elias Harry Lampes - Lynn MA
Craig Robert Jacobson - Peabody MA
Robert Francis Manning - Newburyport MA
Craig Robert Jacobson - Peabody MA
Robert Francis Manning - Newburyport MA
Assignee:
General Electric Company
International Classification:
F01D 518
US Classification:
416 97R
Abstract:
A turbine blade includes an airfoil having opposing first and second sides and an internal passage extending longitudinally therebetween. A plurality of first turbulator ribs extend from the first side into the passage, and a plurality of second turbulator ribs extend from the second side into the passage. The first and second ribs are different in configuration from each other for obtaining different heat transfer enhancements on the first and second sides for reducing pressure losses and cooling air flow requirements.
Crack Arresting Rotor Blade
US Patent:
5902093, May 11, 1999
Filed:
Aug 22, 1997
Appl. No.:
8/916386
Inventors:
Gary C. Liotta - Beverly MA
Paul J. Acquaviva - Maldon MA
Leston M. Freeman - S. Hamilton MA
Robert F. Manning - Newburyport MA
Paul J. Acquaviva - Maldon MA
Leston M. Freeman - S. Hamilton MA
Robert F. Manning - Newburyport MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
B63H1/14
US Classification:
416 97R
Abstract:
A rotor blade includes a dovetail and an airfoil joined thereto. The airfoil includes first and second spaced apart sides joined together laterally at opposite leading and trailing edges, and spanwise at a root and opposite tip. A serpentine cooling circuit extends inside the airfoil for channeling air therethrough for cooling the blade. The serpentine circuit includes first and second passes and a first bend therebetween for firstly receiving the cooling air in turn from the dovetail. A tip circuit is disposed between the tip and the serpentine circuit at the first bend for separating the tip from the first bend and providing cooling thereof near the trailing edge.
Method For Preventing Backflow And Forming A Cooling Layer In An Airfoil
US Patent:
2008015, Jun 26, 2008
Filed:
Dec 21, 2006
Appl. No.:
11/643415
Inventors:
Jack Raul Zausner - Niskayuna NY, US
David James Walker - Burnt Hills NY, US
Robert Francis Manning - Newburyport MA, US
David James Walker - Burnt Hills NY, US
Robert Francis Manning - Newburyport MA, US
International Classification:
F01D 5/12
US Classification:
415 1
Abstract:
The present invention relates to a method for preventing backflow and forming a cooling layer in an airfoil by creating separation regions at a cooling slot inlet and flowing cooling fluid through the cooling slot.
Crossflow Turbine Airfoil
US Patent:
8210814, Jul 3, 2012
Filed:
Jun 18, 2008
Appl. No.:
12/141238
Inventors:
Jack Raul Zausner - Evanston IL, US
David James Walker - Burnt Hills NY, US
Robert Francis Manning - Newburyport MA, US
David James Walker - Burnt Hills NY, US
Robert Francis Manning - Newburyport MA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 5/18
US Classification:
416 97R
Abstract:
A turbine airfoil includes pressure and suction sidewalls extending axially in chord between opposite leading and trailing edges. The sidewalls are spaced transversely apart to define flow channels extending longitudinally and separated chordally by partitions bridging the sidewalls. A perforate partition includes a row of crossover holes extending obliquely therethrough.
Stepped Outlet Turbine Airfoil
US Patent:
7246999, Jul 24, 2007
Filed:
Oct 6, 2004
Appl. No.:
10/959615
Inventors:
Robert Francis Manning - Newburyport MA, US
Thomas Edward Demarche - Boxford MA, US
David Allen Flodman - Rowley MA, US
Thomas Edward Demarche - Boxford MA, US
David Allen Flodman - Rowley MA, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
B63H 1/14
US Classification:
416 97R, 415115, 415116
Abstract:
A turbine airfoil includes an internal cooling circuit between opposite pressure and suction sidewalls. The pressure sidewall includes a row of outlet slots for the circuit separated by converging partitions. Each slot includes an inlet, throat, and diverging outlet. Each of the partitions includes a step in a converging sidewall thereof for increasing divergence of the slots to diffuse coolant discharged therethrough.
Cool Tip Blade
US Patent:
6164914, Dec 26, 2000
Filed:
Aug 23, 1999
Appl. No.:
9/379023
Inventors:
Victor H. S. Correia - Milton Mills NH
Robert F. Manning - Newburyport MA
Robert F. Manning - Newburyport MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F01D 518, F01D 520
US Classification:
416 97R
Abstract:
A turbine blade includes a hollow airfoil having a squealer tip rib extending outboard from a tip cap enclosing the airfoil. An impingement baffle is spaced inboard from the tip cap to define a tip plenum therebetween. Impingement holes extend through the baffle and are directed at the junction of the rib and cap for impinging a coolant jet thereagainst.