Opra Technologies B.v.

Hija Holding B.v.

R Jan Mowill

Marek Dvorak

Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

Apparatus and method for reducing air mass flow for extended range low emissions combustion for single shaft gas turbines

Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases. The turbine is rotatable about an axis for expanding the combustion gases to produce work. The apparatus includes a subassembly of plurality of nozzle guide vanes fixed between a pair of spaced apart, ring-shaped sidewalls. A pair of spaced apart supports is configured to position the subassembly therebetween, concentric with the axis, and adjacent the turbine inlet. The apparatus further includes a plurality of bolt assemblies extending axially through the pair of supports, apertures in the sidewalls, and holes in the guide vanes. The sidewall apertures and guide vane holes each have an internal dimension in the radial direction sized and configured to accommodate thermal expansion and/or contraction sliding radial movement of the subassembly relative to the supports.

Turbine inlet nozzle guide vane mounting structure for radial gas turbine engine

A gas turbine engine with a single stage combustor includes an external premixer to provide premixed fuel/compressed air to the combustor as well as compressed air for dilution; and an automatic controller to provide feedback control of the compressed air flow and fuel flow to the premixer in accordance with actual power versus power demand. The fuel/compressed air mixture is combusted in a combustor and the combustion gases and dilution air are expanded in a turbine. The engine further includes a bleed valve under control of the controller for diverting sufficient compressed dilution air past the turbine to induce increased fuel flow and compressed air flow to the premixer for delivery to, and combustion of, the combustor to compensate for the power deficit due to the bled air, to provide selected minimum premixer exit velocities during engine operation.

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Hengelo, Netherlands

R Jan Mowill