A main stage fuel mixer that reduces NO 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 Nox (DLN) combustors

A method of diffusing airflow includes diffusing first and second airflow portions at first and second diffusion rates, respectively, which are unequal for improving pressure recovery. An exemplary diffuser for practicing the invention includes first and second channels separated by a splitter for separately diffusing first and second airflow portions, respectively. The first and second channels have first and second area ratios, respectively, which are unequal for obtaining increased pressure recovery. In the preferred embodiment, the first and second area ratios are preselected for obtaining substantially symmetrical airflow streamlines over a leading edge of the splitter.

Profile matched diffuser

A combustion device used in gas turbine engines includes an annular combustor that contains the combustion process of air and fuel and then guides the hot gas products to a first stage turbine subsection of a gas turbine engine. The annular combustor has an inner/outer shell having corrugated surfaces that extend radially outward and inward across an entire hot gas stream inside the annular combustor. The corrugations twist about the engine centerline in a longitudinal direction of travel of the engine. The resulting flow path accelerates and turns the hot gas stream to conditions suitable for introduction into the first stage turbine blades, which eliminate the need for first stage turbine vanes. The annular combustor is configured with a system of fuel and air inlet passages and nozzles that results in a staged combustion of premixed fuel and air.

Tangential combustor with vaneless turbine for use on gas turbine engines

An improved diffuser for a gas turbine engine is mounted between a compressor section and a burner section The diffuser eliminates struts by using the exit guide vanes of the compressor for support The vanes are fixedly mounted to an inner case wall and to a double outer wall A cantilevered case wall being one of the double outer walls can flex both radially and axially to relieve thermal stress in the vanes Additionally, probes can be mounted in access ports formed in the double outer wall Compressor leakage gas is prevented from entering voids in the double outer wall by a seal seated between the cantilevered case wall and the outer case wall

Strutless diffuser for gas turbine engine

The pilot burner for a high MN inlet burner is folded to substantially reduce the overall length of the combustor. The annular burner includes a splitter design where a diffuser surrounds the burner and connects to an outer shroud which contains the inlet of the pilot burner. Flow reverses into the pilot burner where it is directed to the primary burning zone of the combustion chamber.

Folded-over pilot burner

An annular pilot combustor for a turbine type power plant includes radial inflow air and fuel nozzles judiciously oriented to improve heat load characteristics, eliminate a diffuser passage and shorten the overall combustor and supporting parts.

Radial inflow combustor

This invention is for a turbine type power plant which includes a swirl-type annular burner and is concerned with diverting a portion of compressor air from the compressor discharge flow stream where it is utilized for cooling and dilution in the burner and is particularly concerned with the construction of the diffuser section

Paul B. Greenberg

Papers

Radial inflow combustor

Combustor diffuser for turbine type power plant and construction thereof