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Gabriel L Suciu

from Brighton, MA
Age ~71
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Also known as:
Gabriel D Suciu, Gabriel M Suciu, Gabriel L Sucio, Gabriel L Sociu, Gabriell Suciu
Connected to:
Annemarie Suciu, 34Cecelia E Suciu, 51Corneliu Suciu, 62David J Suciu, 52George Suciu, 98Mariana Suciu, 52Amy N Suckarieh, 46Jessica L Suckau, 33Tania T Suckie, 49Shane O Suckla, 55

Gabriel Suciu Phones & Addresses

  • Brighton, MA
  • 17 Tanglewood Dr #B5, Glastonbury, CT 06033 (860) 633-7822
  • 27 Tanglewood Dr, Glastonbury, CT 06033 (860) 633-7822 (860) 657-4781
  • 38 Rambling Brook Ln #C8, Glastonbury, CT 06033 (860) 633-7822
  • 38 Rambling Brook Ln, Glastonbury, CT 06033
  • 100 Oxbow Dr #C8, Glastonbury, CT 06033 (860) 633-7822
  • 85 Oxbow Dr #C5, Glastonbury, CT 06033 (860) 633-7822
  • 100 Oxbow Dr, Glastonbury, CT 06033
  • 85 Oxbow Dr, Glastonbury, CT 06033
  • 235 Stanley Dr, Glastonbury, CT 06033 (860) 633-7822
  • 56 Willieb St #56, Glastonbury, CT 06033 (860) 633-7822
  • 56 Willieb St, Glastonbury, CT 06033
  • 12 Stony Brook Dr #B1, Glastonbury, CT 06033 (860) 633-7822
  • 17 Stony Brook Dr #B5, Glastonbury, CT 06033 (860) 633-7822
  • 30 Stony Brook Dr #B4, Glastonbury, CT 06033 (860) 633-7822
  • Brookline, MA
  • Storrs Mansfield, CT

Publications

Us Patents

Blade For Turbine Engine

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US Patent:
6764282, Jul 20, 2004
Filed:
Nov 14, 2001
Appl. No.:
09/991149
Inventors:
Gabriel L. Suciu - Glastonbury CT
Michael Babu - Fairfield CT
James R. Murdock - Tolland CT
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 532
US Classification:
416220R, 416223 A, 416243
Abstract:
A blade for a turbine engine having a centerline. The blade comprises: a root section extending at an angle relative to the centerline; and an airfoil section extending from the root section. The root section is directly adjacent said airfoil section. In other words, the blade is neckless. The blade is part of a rotor assembly, and is preferably a fan blade.

Turbine Engine Disk Spacers

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US Patent:
7059831, Jun 13, 2006
Filed:
Apr 15, 2004
Appl. No.:
10/825255
Inventors:
Gabriel L. Suciu - Glastonbury CT, US
James W. Norris - Lebanon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/06
US Classification:
4151995, 416198 A, 416244 A
Abstract:
A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.

Turbine Engine Rotor Retainer

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US Patent:
7147436, Dec 12, 2006
Filed:
Apr 15, 2004
Appl. No.:
10/825256
Inventors:
Gabriel L. Suciu - Glastonbury CT, US
James W. Norris - Lebanon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 25/00
F04D 29/20
US Classification:
4152161, 416198 A, 416244 A
Abstract:
A gas turbine engine has a rotor stack carried by a central shaft. A number of retainer segments each have a first surface engaging the rotor stack and a second surface engaging the central shaft so as to transmit a precompression force from the central shaft to the rotor stack.

Turbine Engine Disk Spacers

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US Patent:
7186079, Mar 6, 2007
Filed:
Nov 10, 2004
Appl. No.:
10/985863
Inventors:
Gabriel L. Suciu - Glastonbury CT, US
James W. Norris - Lebanon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/06
US Classification:
4151995, 416198 A, 416244 A
Abstract:
A gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The spacers may provide a longitudinal compression force that increases with rotational speed.

Seal Arrangement For A Fan-Turbine Rotor Assembly

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US Patent:
7201558, Apr 10, 2007
Filed:
May 5, 2005
Appl. No.:
11/122368
Inventors:
James W. Norris - Lebanon CT, US
Craig A. Nordeen - Manchester CT, US
Gary Roberge - Tolland CT, US
Gabriel Suciu - Glastonbury CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F04D 31/00
US Classification:
415110, 415116, 416219 R
Abstract:
A fan-turbine rotor hub includes an outer periphery scalloped by a multitude of elongated openings. Each elongated opening defines an inducer receipt section to receive an inducer section and a hollow fan blade section. An inducer exit from each inducer section is located adjacent a core airflow passage within each fan blade section to provide communication therebetween. A seal is located between an inner fan blade mount and a blade receipt section to minimize airflow leakage between the inducer exit and the core airflow passage.

Bleed Housing

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US Patent:
7249929, Jul 31, 2007
Filed:
Nov 13, 2003
Appl. No.:
10/713641
Inventors:
Kevin J. Cummings - West Hartford CT, US
Christopher G. Demers - Willington CT, US
James C. Hodgson - Canton CT, US
Gabriel Suciu - Glastonbury CT, US
Brian Merry - Andover CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 25/14
US Classification:
415144, 415145, 4152112, 2988922
Abstract:
A gas turbine engine compressor has a number of shroud rings, at least a bleed one of which defines a number of bleed ports. A structural hub is downstream of the shroud rings and secured relative to the shroud rings. A structural hub case extends from an aft joint with the structural hub to a fore joint with a joined one of the shroud rings and has a number of valve ports. At least a portion of the structural case extends structurally between the fore and aft joints. A valve element is shiftable between first and second conditions for respectively blocking and not blocking communication through the valve ports.

Turbine Engine Rotor Stack

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US Patent:
7309210, Dec 18, 2007
Filed:
Dec 17, 2004
Appl. No.:
11/016453
Inventors:
Gabriel L. Suciu - Glastonbury CT, US
James W. Norris - Lebanon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 5/10
US Classification:
4151742, 415196 R
Abstract:
A turbine engine has a first disk and a second disk, each extending radially from an inner aperture to an outer periphery. A coupling, transmits a torque and a longitudinal compressive force between the first and second disks. The coupling has first means for transmitting a majority of the torque and a majority of the force and second means, radially outboard of the first means, for vibration stabilizing.

Turbine Engine Disk Spacers

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US Patent:
7322101, Jan 29, 2008
Filed:
Apr 21, 2006
Appl. No.:
11/408453
Inventors:
Gabriel L. Suciu - Glastonbury CT, US
James W. Norris - Lebanon CT, US
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F01D 1/02
F01D 9/00
US Classification:
298892, 294011, 4151995
Abstract:
A gas turbine engine rotor stack may be engineered or reengineered to include one or more longitudinally outwardly concave spacers. The spacers may provide a longitudinal compression force that increases with rotational speed.
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Gabriel L Suciu from Brighton, MA, age ~71 Get Report