Westinghouse Electric Corporation

Siemens Westinghouse Power Corporation

David J Amos

Mitchell O Stokes

Eugenio Colautti

Anthony McWhirter

David Marchant Parker

Donald M Newburry

David T Foss

Perry E Lowe

Richard Hobert Bunce

Taku Ichiryu

Tomohiko Sato

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. The turbulence results in greater interaction between main and pilot combustion zones, consequently reducing NO.sub.x /CO emissions.

Pilot cones for dry low-NO.sub.x combustors

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.

Main stage fuel mixer with premixing transition for dry low No.sub.x

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.

Combustor with flashback arresting system

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.

Gas turbine ultra low NOx combustor

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.

Gas turbine combustor

Gas turbine combustor swirl vane arrangement

A two shaft gas turbine engine is shown wherein the power turbine comprises a single stage which is closely coupled to the compressor turbine through an annular transition portion having radially diverging side walls forming an inner and outer shroud. The relatively high velocity of the working fluid is maintained through the transition portion by an array of non-rotating stationary struts. Each strut defines a camber line which at the entry of the strut is angled to receive the working fluid, having a swirl component therein, at a 0.degree. angle of incidence. Further, each strut has a configuration which, in cooperation with the increasing angle of the camber line compensates for the divergence of the shrouds to maintain the flow of the working fluid at a generally undiminished velocity therethrough. An array of non-rotating variable vanes is disposed intermediate the downstream end of the struts to direct the working fluid into the power turbine at an optimum angular discharge depending upon the desired output of the power turbine shaft.

Intermediate transition annulus for a two shaft gas turbine engine

A vane assembly is shown for a relatively short annular transition zone directing the discharge of the working fluid from the compressor turbine to a single stage power turbine in a gas turbine engine. The annular transition zone comprises a plurality of individual arcuate segments having a pair of stationary vanes integrally molded to inner and outer shroud members. A variable vane is disposed immediately downstream of each stationary vane for guiding the working fluid into the power turbine at an optimum angle. The variable vanes are manually adjustable from outside the turbine casing through a linkage and support mechanism that maintains a constant clearance between the variable vane and the shroud members and also accommodates variations in dimensional relationships due to temperature variations. Also, provision is made for centering the axis of the variable vanes to a precise position with respect to the stationary vane to accommodate the buildup of assembly tolerances.

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Orlando, FL, United States of America

David J Amos