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Perry Tracie Lowe

from Orlando, FL
Age ~57

Perry Lowe Phones & Addresses

  • 5026 Cassatt Ave, Orlando, FL 32808 (407) 294-2528 (407) 297-5719
  • Rowland Heights, CA
  • Brooklyn, NY
  • Rowland Heights, CA
  • Los Angeles, CA
  • Montclair, CA

Publications

Us Patents

Apparatus And Method For Supporting The Torque Load On A Gas Turbine Vane

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US Patent:
49574124, Sep 18, 1990
Filed:
Sep 6, 1988
Appl. No.:
7/240292
Inventors:
Rick A. Olson - Apopka FL
Perry E. Lowe - Altamonte Springs FL
Assignee:
Westinghouse Electric Corp. - Pittsburgh PA
International Classification:
F01D 2524
US Classification:
415189
Abstract:
A gas turbine of the type having turbine vanes retained in a cylinder and utilizing torque pins to transmit the torque load on the vanes to the cylinder is provided with improved structure for enabling insertion and withdrawal of the pin from engagement with the outer vane shroud in the vicinity of the cylinder flanges.

Turbomachine Rotor With Improved Cooling

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US Patent:
57555567, May 26, 1998
Filed:
May 17, 1996
Appl. No.:
8/649507
Inventors:
Kent Goran Hultgren - Winter Park FL
Leroy Dixon McLaurin - Winter Springs FL
Oran Leroy Bertsch - Titusville FL
Perry Eugene Lowe - Oviedo FL
Assignee:
Westinghouse Electric Corporation - Pittsburgh PA
International Classification:
F04D 2958
US Classification:
416 96R
Abstract:
A gas turbine rotor has an essentially closed loop cooling air scheme in which cooling air drawn from the compressor discharge air that is supplied to the combustion chamber is further compressed, cooled, and then directed to the aft end of the turbine rotor. Downstream seal rings attached to the downstream face of each rotor disc direct the cooling air over the downstream disc face, thereby cooling it, and then to cooling air passages formed in the rotating blades. Upstream seal rings attached to the upstream face of each disc direct the heated cooling air away from the blade root while keeping the disc thermally isolated from the heated cooling air. From each upstream seal ring, the heated cooling air flows through passages in the upstream discs and is then combined and returned to the combustion chamber from which it was drawn.

Gas Turbine Combustor

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US Patent:
54797829, Jan 2, 1996
Filed:
Oct 7, 1994
Appl. No.:
8/319686
Inventors:
David M. Parker - Oviedo FL
David T. Foss - Winter Park FL
Perry E. Lowe - Winter Park FL
David J. Amos - Orlando FL
Assignee:
Westinghouse Electric Corporation - Pittsburgh PA
International Classification:
F02C 920
US Classification:
60747
Abstract:
A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages, each of which has a circumferential array of individually rotatable swirl vanes. The swirl vanes are mounted on axially oriented primary fuel pegs that extend through the air inlet passages. The middle and outer liners form an outer annular passage in which radially oriented secondary fuel pegs are disposed. The middle and inner liners form an inner annular passage that is supplied with cooling air. A perforated circumferentially extending baffle is locating in the inner annular passage and directs the cooling air to flow over the inner liner.
Perry Tracie Lowe from Orlando, FL, age ~57 Get Report