Abstract: A turbine engine has a case with an axis. A fan is mounted for rotation about the axis. A turbine is mechanically coupled to the fan to drive rotation of the fan about the axis. A number of compressor/turbine units are downstream of the fan and upstream of the turbine along a core flowpath. A number of compressors are coupled to the compressor/turbine units to receive air and deliver combustion gas to drive the turbine.

Abstract: A turbine engine has a case with an axis. A fan is mounted for rotation about the axis. A turbine is mechanically coupled to the fan to drive rotation of the fan about the axis. A number of compressor/turbine units are downstream of the fan and upstream of the turbine along a core flowpath. A number of compressors are coupled to the compressor/turbine units to receive air and deliver combustion gas to drive the turbine.

Abstract: Accordingly, the present invention provides a ducting system for use on a gas turbine engine having two fans connected to a common shaft, and includes a primary inlet duct that is integral with a plurality of primary discharge ducts, a plurality of secondary inlet ducts that are integral with a secondary discharge duct, each of the ducts includes a port, the ports of the secondary inlet ducts are located radially outward of the port of the primary inlet duct, and the ports of the primary discharge ducts are located radially outward of the port of the secondary discharge duct.

Abstract: A variable cycle gas turbine engine (10) includes a core unit (30) having a guide vane array (36), and a hybrid stage (38) with a rotor blade array (40) and a stator vane array (42). The engine is operable in at least two modes which channel different quantities of working medium air to the core unit, and each mode corresponds to a distinct thermodynamic cycle. The vanes (54) of the hybrid stage stator vane array are bivariable so that the leading segment (140) and trailing segment (146) of each vane are separately adjustable over a range of pitch angles. The bivariable character of the vanes ensures aerodynamic stability of the engine in each of its modes of operation.

Abstract: A separate low pressure shaft and a high pressure shaft are axially aligned. The low pressure shaft is at one end and carries the low pressure compressor and the low pressure turbine, and is connected to the electric generator. The high pressure shaft carries the high pressure compressor and the high pressure turbine. Only three bearing housings are required. Parts of the casing are horizontally split to simplify maintenance.

Abstract: In a humid air gas turbine cycle the compressed air is humidified prior to introduction to the combustor. Compressed air before humidification is used to cool the first turbine stage rotor blades. Humidified air is used to cool the first turbine stage stationary vanes.

Abstract: For barbequeing food, a portable cooker, convertible for both indoor and outdoor use, is provided. The burner of a gas or electric kitchen stove is used to fire the cooker indoors, whereas charcoal or other combustible fuel is used as a source of heat for outdoor use. Two embodiments of the version are disclosed, one adapted for single burner indoor use and the other adapted for twin or dual burner indoor use. The second embodiment employs internal baffles for equal distribution of the applied heat. Both embodiments include an effective grease collection system for intercepting and drawing off a portion of the grease drippings.