Processes for generating electric power are provided. The processes involve combining a supercritical water stream with a pressurized, heated hydrocarbon-based composition in a mixing device to create a combined feed stream. The combined feed stream is introduced to a supercritical reactor to produce an upgraded product. The upgraded product is depressurized and separated. The upgraded product may be separated into a light and heavy fraction where the light may be introduced to a gas turbine to generate electric power and the heavy fraction may be introduced to a boiler to generate electric power, or both. Alternatively, the depressurized upgraded product may be further separated to produce a fuel oil fraction comprised of cutterstock and a heavy fraction which may be passed to a boiler to generate electric power, and a light fraction, which may be passed to a gas turbine system to generate electric power, or both.

Processes for generating electric power are provided. The processes involve combining a supercritical water stream with a pressurized, heated hydrocarbon-based composition in a mixing device to create a combined feed stream. The combined feed stream is introduced to a supercritical reactor to produce an upgraded product. The upgraded product is depressurized and separated. The upgraded product may be separated into a light and heavy fraction where the light may be introduced to a gas turbine to generate electric power and the heavy fraction may be introduced to a boiler to generate electric power, or both. Alternatively, the depressurized upgraded product may be further separated to produce a fuel oil fraction comprised of cutterstock and a heavy fraction which may be passed to a boiler to generate electric power, and a light fraction, which may be passed to a gas turbine system to generate electric power, or both.

A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.

A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.

Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud. Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud. Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

A turbine section for a gas turbine engine includes a variable reaction free wheel downstream of the first static vane structure and a turbine rotor downstream of the variable reaction free wheel. A method of generating thrust for a gas turbine engine, includes rotating a variable reaction free wheel located downstream of a combustor and upstream of a turbine rotor to augment a swirl of a core flow combustion gases.

The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.

A method machines or tests a blade for a turbomachine. The method includes: clamping the blade in a clamp such that a point contact or a line contact forms between the blade and the clamp as clamping partners. One of the clamping partners has a lower strength than the other clamping partner and plasticizes in the region of the point contact or the line contact.