An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and method of operation improves operation of the turbine.

An improved combustor for a gas turbine is operable to provide high combustion efficiency in a compact combustion chamber. The combustor includes a counter swirl doublet for improved fuel/air mixing. The enhanced combustor assembly and method of operation improves operation of the turbine.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.

The invention is characterized by a rotary external housing and the attachment of the movable blades to the inner side of said housing, and by the attachment of the fixed (or static) blades to a shaft or other static central element, irrespective of whether compression or expansion occurs in one or more stages. The proposed attachment eliminates the radial gap in the region that transfers maximum energy to the fluid, thereby drastically reducing the problems due to stalling at the boundary layer. In this way, there is no drop in the mechanical performance of small axial turbines and compressors with a less favorable ratio of radial gap to housing diameter, an aspect that has prevented more generalized use thereof. The fixed blades, by not transferring energy to the fluid and decelerating the rotation thereof, encounter fewer stalling problems than movable blades.

A composition comprising trifluoroiodomethane (CF.sub.3I) and 1,1-difluoroethylene (R-1132a) is described. The composition can also comprise additional compounds, such as at least one non-flammable compound selected from the group consisting of carbon dioxide (CO2; R-744), tetrafluoromethane (R-14), trifluoromethane (R-23) and perfluoroethane (R-116) or at least one additional compound of lower volatility than 1,1-difluoroethylene selected from the group consisting of 1,1,2-trifluoroethylene (R-1123), difluoromethane (R-32), propane (R-290), propylene (R-1270), fluoroethane (R-161), pentafluoroethane (R-125), 1,1,1,2-tetrafluoroethane (R-134a), 2,3,3,3-tetrafluopropene (R-1234yf), isobutane (R-600a), n-butane (R-600), trans-1,3,3,3-tetrafluopropene (R-1234ze(E)), 3,3,3-trifluoropropene (R-1243zf), 1,2,3,3,3-pentafluoropropene (R-1225ye), 1, 1,1,2,3,3,3-heptafluoropropane (R-227ea), 1,1- difluoroethane (R-152a), cis-1,3,3,3-tetrafluopropene (R-1234ze(Z)), 1-chloro-3,3,3-trifluoropropene (R-1233zd(E/Z)) and 1,1,1,4,4,4-hexafluoro-2-butene (R-1336mzz(E/Z)). The compositions have utility as refrigerants in vapour compression heat transfer systems.

A composition comprising trifluoroiodomethane (CF.sub.3I) and 1,1-difluoroethylene (R-1132a) is described. The composition can also comprise additional compounds, such as at least one non-flammable compound selected from the group consisting of carbon dioxide (CO2; R-744), tetrafluoromethane (R-14), trifluoromethane (R-23) and perfluoroethane (R-116) or at least one additional compound of lower volatility than 1,1-difluoroethylene selected from the group consisting of 1,1,2-trifluoroethylene (R-1123), difluoromethane (R-32), propane (R-290), propylene (R-1270), fluoroethane (R-161), pentafluoroethane (R-125), 1,1,1,2-tetrafluoroethane (R-134a), 2,3,3,3-tetrafluopropene (R-1234yf), isobutane (R-600a), n-butane (R-600), trans-1,3,3,3-tetrafluopropene (R-1234ze(E)), 3,3,3-trifluoropropene (R-1243zf), 1,2,3,3,3-pentafluoropropene (R-1225ye), 1, 1,1,2,3,3,3-heptafluoropropane (R-227ea), 1,1- difluoroethane (R-152a), cis-1,3,3,3-tetrafluopropene (R-1234ze(Z)), 1-chloro-3,3,3-trifluoropropene (R-1233zd(E/Z)) and 1,1,1,4,4,4-hexafluoro-2-butene (R-1336mzz(E/Z)). The compositions have utility as refrigerants in vapour compression heat transfer systems.

A multi-source aircraft propulsion arrangement comprises a cryogenic propulsion source and a combustion propulsion source wherein the cryogenic propulsion source and the combustion propulsion source may be selectively and independently operated to generate propulsive force for an aircraft.

A method for installing a gas turbine assembly of a first type at a position of an existing power plant where previously a gas turbine assembly of a second type was installed on a foundation specially designed for said second type. The gas turbine assembly includes at least one housing, a compressor, a combustion chamber, a gas turbine, and a plurality of venting and removal lines guided along the exterior of the housing. Modifications to the venting and/or removal lines of the gas turbine assembly of the first type are carried out in a first step, and the modified gas turbine assembly is installed on the existing foundation in a second step.

An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.