General Electric Company

Stephen Hugh Black

William Theodore Bechtel

Lewis Berkley Davis, Jr

Allen Michael Ritter

Anthony John Dean

John Luigi Battaglioli

Andrew Luts

Rahul Jaikaran Chillar

John William Herbold

Robert Joseph Iasillo

Robert James Bland

James Rollins Maughan

Michael Alan Davi

David Orus Fitts

Vrinda Rajiv

Richard Sterling Tuthill

Daniel Mark Brown

Guy Wayne DeLeonardo

Mark Mitchell Kornfein

Philippe Giguere

Anthony J Loprinzo

Jeffrey Arthur Benoit

Joseph Charles Taura

Adam Lord

Stefan Martin Meyer

H Lindsay Morton

Brian Andreson

Michael R Lablanc

A clamp assembly for facilitating attachment and removal of a first component to or from a second component includes plural clamp bodies, each having at least two mutually perpendicular surfaces arranged about the first component. A substantially rigid ring is located between one surface of the clamp body and a surface of the first component. At least one fastener is provided for each of the plural clamp bodies, adapted to extend through a respective one of the plural clamp bodies and into the second component. Tooling is provided to allow for simultaneous tightening or loosening of all bolts on a single combustor.

Quick disconnect combustion endcover

A combustor for a turbine includes a combustor liner; a first flow sleeve surrounding the liner, the flow sleeve having a plurality of rows of cooling holes formed about a circumference of the flow sleeve; and a transition piece connected to the combustor liner and the flow sleeve and adapted to carry hot combustion gases to a stage of the turbines. The transition piece is surrounded by a second flow sleeve which directs cooling air to the transition piece. One of the plurality of rows of cooling holes in the first flow sleeve is located adjacent the transition piece, and cooling conduits are mounted in the cooling holes of at least the first of the plurality of rows of cooling holes to direct impingement cooling air against the surface of the liner while diverting crossflow cooling air around the impingement cooling air. A related method of cooling a combustor liner of a gas turbine combustor with a flow sleeve surrounding the liner in substantially concentric relationship therewith includes the steps of a) providing a plurality of axially spaced rows of cooling holes in the flow sleeve, each row extending circumferentially of the flow sleeve, a first of the rows adjacent a forward or downstream end of the flow sleeve; b) locating a plurality of cooling conduits in the cooling holes of at least the first of the rows, the cooling conduits extending radially towards, but not engaging, the liner; and c) supplying cooling air to the annulus such that the cooling conduits direct the cooling air against the liner.

Combustor liner cooling thimbles and related method

A burner for use in a combustion system of a heavy-duty industrial gas turbine includes a fuel/air premixer having an air inlet, a fuel inlet, and an annular mixing passage. The fuel/air premixer mixes fuel and air into a uniform mixture for injection into a combustor reaction zone. The burner also includes an inlet flow conditioner disposed at the air inlet of the fuel/air premixer for controlling a radial and circumferential distribution of incoming air. The pattern of perforations in the inlet flow conditioner is designed such that a uniform air flow distribution is produced at the swirler inlet annulus in both the radial and circumference directions. The premixer includes a swozzle assembly having a series of preferably air foil shaped turning vanes that impart swirl to the airflow entering via the inlet flow conditioner. Each air foil contains internal fuel flow passages that introduce natural gas fuel into the air stream via fuel metering holes that pass through the walls of the air foil shaped turning vanes. By injecting fuel in this manner, an aerodynamically clean flow field is maintained throughout the premixer. By injecting fuel via two separate passages, the fuel/air mixture strength distribution can be controlled in the radial direction to obtain optimum radial concentration profiles for control of emissions, lean blow outs, and combustion driven dynamic pressure activity as machine and combustor load are varied.

Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion

An apparatus and method of applying active, closed loop control to reduce combustion driven pressure oscillation in a single or multi-chamber combustion system in an industrial gas turbine, to increase operability and life of the parts, and in such a way as to require minimal input power. The invention combines the passive control of a two stage nozzle with active control thereby to reduce the requirements on the control device. This allows selection of a control device which will have an adequate life in an industrial environment and yet require minimal input power.

Apparatus and method for active control of oscillations in gas turbine combustors

The dual-fuel nozzle for a gas turbine and combustor includes a liquid fuel nozzle surrounded by a gas fuel nozzle. A converging sleeve surrounds the converging outer wall of the combined liquid fuel and gaseous nozzle to form a duct of decreasing cross-sectional area in a downstream direction whereby air flow through the duct accelerates toward the conical droplet spray pattern emerging from the liquid fuel nozzle. An inside swirler is located upstream of the liquid fuel tip to swirl the air flowing through the duct. An outer swirler is provided about the downstream end of the sleeve, likewise to swirl air. The accelerated swirling air flow through the duct and outer swirling air flow preclude impingement of oil spray droplets onto metal surfaces of the nozzle and hence prevent carbon deposition thereon which would otherwise be deleterious to the liquid fuel and gaseous nozzles.

Dual-fuel nozzle for inhibiting carbon deposition onto combustor

A cross-fire tube for connecting adjacent combustors in a gas turbine includes a hollow tubular body having couplings at opposite free ends thereof, the hollow tubular body having a substantially circular cross-sectional shape with a maximum diameter region about mid-way between the couplings, tapering in opposite directions to smaller diameters at the free ends. A plurality of purge holes are located in the maximum diameter region.

Tapered cross-fire tube for gas turbine combustors

The dual-fuel nozzle includes a liquid fuel nozzle surrounded by an air/gas premixing cup. The cup has a base comprised of swirler vanes surrounding the outer tube of the liquid fuel nozzle. The tip of the liquid fuel nozzle extends to adjacent the open end of the premixing cup opposite the swirler vanes. The interior surface and outer surface of the premix cup and the tip of the liquid fuel nozzle, respectively, at the outer end of the cup are contoured, i.e., tapered complementarily inwardly to avoid recirculation of air in the annulus between the liquid fuel nozzle and the cup. Air recirculation is also prevented, thereby inhibiting flame holding adjacent the base of the cup by providing a smooth transition for air flow through the openings of the swirler at the base of the cup and into the annulus.

Anti-coking dual-fuel nozzle for a gas turbine combustor

A lean burn gas turbine combustor has a premixer zone receiving compressor discharge air through openings in a combustor liner. A fuel nozzle has an upstream orifice 52, a downstream orifice 56, and a captured response volume 54 therebetween. Upstream orifice 52 affords a high pressure drop for gaseous fuel to approximately the pressure of the compressor discharge air. The low pressure discharge orifice affords a pressure drop comparable to the pressure drop across the openings of the combustor liner for the air supply. The dynamic pressure response characteristics of the fuel and air inlets to the premixer zone are substantially matched to eliminate variations in fuel/air concentration resulting from pressure variations in the premixer zone. The captured response volume between the upstream and downstream orifices is sized sufficiently to store enough fuel to accommodate the mismatch in phase angle of fuel flowing into the captured response volume through the upstream orifice at a first phase angle relative to the phase angle of a pressure forcing function in the premixer zone and fuel flowing out of the captured response volume through the downstream fuel discharge orifice at a second phase angle relative to the phase angle of the pressure forcing function.

Apparatus for reducing fuel/air concentration oscillations in gas

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Duanesburg, NY, United States of America

Stephen Hugh Black