DAVID J AMOS
Engineers in Orlando, FL

6122916, Sep 26, 2000

Jan 2, 1998

9/002546

David J. Amos - Orlando FL
Mitchell O. Stokes - Orlando FL

Siemens Westinghouse Power Corporation - Orlando FL

F23R 314, F23R 334

60747

A gas turbine combustor is provided having a nozzle housing adjacent to a main combustion zone, a diffusion fuel pilot nozzle, at least one main nozzle extending through the nozzle housing and attached thereto, and a parabolic pilot cone projecting from the vicinity of an injection port of the pilot nozzle. The parabolic pilot cone has a diverged end adjacent to the main combustion zone, and a parabolic profile forming a pilot flame zone adjacent to the injection port and the diverged end. The increased volume of the pilot flame zone provide a more stable pilot flame. The more stable pilot flame and leaner fuel/air mixture reduce NO. sub. x /CO emissions. A second gas turbine combustor is provided having a fluted pilot cone. The fluted pilot cone has an undulated diverged end adjacent to the main combustion zone forming a pilot flame zone adjacent to the injection port and the undulated diverged end. The undulated diverged end of the fluted pilot cone creates turbulence in the main combustion zone.

5361586, Nov 8, 1994

Apr 15, 1993

8/046320

Anthony McWhirter - Niagara Falls, CA
Eugenio Colautti - Mississauga, CA
David J. Amos - Orlando FL

Westinghouse Electric Corporation - Pittsburgh PA

F23R 332

60737

A gas turbine combustor having a pre-mixing zone and a combustion zone separated by a barrier plate. A plurality of concentrically arranged annular passages, into which lean mixtures of fuel and air are introduced, are disposed in the pre-mixing zone. Each of the annular passages has a discharge end in which a plurality of swirlers are circumferentially arranged that allow fuel/air mixtures flowing through the annular passages to enter the combustion zone, the swirlers acting as flame holders. A toroidal fuel manifold upstream of each of the annular passages allows the fuel/air ratio in each annular passage to be individually controlled. The firing temperature of the combustor is increased by sequentially supplying fuel to each annular passage in turn, with the innermost passages being supplied with fuel first. A pilot fuel assembly is centrally disposed with respect to the annular passages and has swirler vanes and an ignitor.

5713206, Feb 3, 1998

Oct 17, 1994

8/623059

Anthony McWhirter - Niagara Falls, CA
Eugenio Colautti - Mississauga, CA
David J. Amos - Orlando FL

Westinghouse Electric Corporation - Pittsburgh PA

F23R 332

60747

A gas turbine combustor having a pre-mixing zone and a combustion zone separated by a barrier plate. A plurality of concentrically arranged annular passages, into which lean mixtures of fuel and air are introduced, are disposed in the pre-mixing zone. Each of the annular passages has a discharge end in which a plurality of swirlers are circumferentially arranged that allow fuel/air mixtures flowing through the annular passages to enter the combustion zone, the swirlers acting as flame holders. A toroidal fuel manifold upstream of each of the annular passages allows the fuel/air ratio in each annular passage to be individually controlled. The firing temperature of the combustor is increased by sequentially supplying fuel to each annular passage in turn, with the innermost passages being supplied with fuel first. A pilot fuel assembly is centrally disposed with respect to the annular passages and has swirler vanes and an ignitor.

6038861, Mar 21, 2000

Jun 10, 1998

9/095234

David J. Amos - Orlando FL
Mitchell O. Stokes - Orlando FL

Siemens Westinghouse Power Corporation - Orlando FL

F02G 300

60737

A main stage fuel mixer that reduces NO. sub. x and CO emissions of a gas turbine combustor by providing a more homogeneous fuel/air mixture for main stage combustion is provided. A gas turbine combustor according to the present invention includes a nozzle housing having a nozzle housing base, a plurality of main nozzles, and a main stage fuel mixer. A main combustion zone is located adjacent to the nozzle housing. Each main nozzle extends through the nozzle housing and is attached to the nozzle housing base. The main stage fuel mixer has a plurality of inlets, each of which is adapted to receive a flow of gas, and an outlet adjacent to the main combustion zone. The main stage fuel mixer has a plurality of transition ducts, each associated with one inlet. Each transition duct provides fluid communication from the inlet associated with the transition duct to the outlet.

5857320, Jan 12, 1999

Nov 12, 1996

8/746328

David Joseph Amos - Orlando FL
Donald Maurice Newburry - Orlando FL
Richard Hobert Bunce - Altamonte Springs FL

Westinghouse Electric Corporation - Pittsburgh PA

F02C 926

60 3906

A combustor with a flashback arresting system for producing a hot gas by burning premixed fuel and compressed air having fuel/air premixing passages, each of the passages having an inlet end and a discharge end. Disposed immediately upstream of the inlet ends of the fuel/air premixing passages is a fuel manifold for delivering fuel to the passages. Fuel lines with fuel flow control valves connect the fuel manifold with a fuel supply. The flashback arresting system has one or more optical flame detectors with a light receiving portion located upstream of the discharge ends of the fuel/air premixing passages and oriented toward at least a portion of at least one of the fuel/air passages. The flame detectors are responsive to receiving light from a flashback by its light receiving portion by transmitting an output signal to a control system. The control system controls the fuel flow control valves and responds to the output signal by adjusting the fuel flow control valves to eliminate the flashback.

5479782, Jan 2, 1996

Oct 7, 1994

8/319686

David M. Parker - Oviedo FL
David T. Foss - Winter Park FL
Perry E. Lowe - Winter Park FL
David J. Amos - Orlando FL

Westinghouse Electric Corporation - Pittsburgh PA

F02C 920

60747

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.

2002015, Oct 31, 2002

Apr 27, 2001

09/842881

Wilhelm Schulten - Essen, DE
Gerhard Simon - Essen, DE
Peter Tiemann - Witten, DE
David Amos - Orlando FL, US
Hans Maghon - Muelheim, DE

Siemens Aktiengesellschaft

F23R003/42

060/772000, 060/039370

A gas turbine is provided which has a combustor comprising a plurality of can-type combustor elements and an annular element. Isolated combustion takes place in the can-type combustor thereby generating individual component hot gas streams. The component hot gas streams are merged in the annular part. Combustion oscillations are substantially avoided by decoupling combustion flames. Accordingly, temperature and pressure homogenization as well as combustion stabilization by cross-ignition is effected.

5394688, Mar 7, 1995

Oct 27, 1993

8/141757

David J. Amos - Orlando FL

Westinghouse Electric Corporation - Pittsburgh PA

F02C 920, F23R 314

60 3923

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.