Abstract: The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.

Abstract: A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.

Abstract: A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.

Abstract: The present technique presents a blade 1 for a gas turbine 10. The blade 1 includes an airfoil 100 having an airfoil tip part 100a and a pressure side 102 and a suction side 104 meeting at a leading edge 106 and a trailing edge 108 and defining an internal space 100s of the airfoil 100. A squealer tip 80, 90 is arranged at the airfoil tip part 100a. The squealer tip 80, 90 comprises a suction side rail 90. The suction side rail 90 comprises a chamfer part 90x and at least one squealer tip cooling hole 99. The chamfer part 90x comprises a chamfer surface 9. An outlet 99a of the at least one squealer tip cooling hole 99 is disposed at the chamfer surface 9.

Abstract: A method for charging pallet cars of a traveling grate for the thermal treatment of bulk material includes in a first step a first layer is applied as a hearth layer on a grate surface of the pallet car. In at least one second step a second layer at the same time or successively is applied as a side layer on two opposed side walls of the pallet car and a third layer is applied as green pellet layer between the side layers and on the hearth layer. The pellets used for the grate and the side layer differ in terms of their diameter and size distribution.

Abstract: A method for charging pallet cars of a traveling grate for the thermal treatment of bulk material includes in a first step a first layer is applied as a hearth layer on a grate surface of the pallet car. In at least one second step a second layer at the same time or successively is applied as a side layer on two opposed side walls of the pallet car and a third layer is applied as green pellet layer between the side layers and on the hearth layer. The pellets used for the grate and the side layer differ in terms of their diameter and size distribution.

Abstract: A process for preparing a catalyst provided in the form of a metal oxide catalyst having at least one element selected from Mo, Te, Nb, V, Cr, Dy, Ga, Sb, Ni, Co, Pt and Ce. The catalyst is subjected to an aftertreatment to increase the proportion of the M1 phase, by contacting the catalyst with steam at a pressure below 100 bar or by contacting the catalyst with oxygen to obtain an aftertreated catalyst. The aftertreated catalyst may be used for oxidative dehydrogenation processes.

Abstract: An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.

Abstract: The invention relates to a process for preparing linear ?-olefins, wherein ethylene 1a is conducted into the oligomerization reactor 2 in the liquid phase. The oligomerization reactor 2 has a mechanical stirrer 2a in order to ensure optimal mixing of the liquid ethylene and of the catalyst in the liquid phase. From the top of the oligomerization reactor 2, vaporized ethylene is drawn off together with light ?-olefins and a small proportion of the organic solvent. The gas mixture drawn off from the top of the reactor 2 is condensed together with gaseous fresh ethylene 7 by means of heat exchanger 3 and separator 4. The liquid phase drawn off from the separator 4 is conducted by means of circulation pump 5a as liquid ethylene input 1a back into the oligomerization reactor 2. The liquid products of the oligomerization reaction are drawn off 8 laterally from the base of the reactor 2.

Abstract: The present invention relates to a method for oligomerization of ethylene, comprising the steps: a) feeding ethylene, solvent and a catalyst composition comprising catalyst and cocatalyst into a reactor, b) oligomerizing ethylene in the reactor, c) discharging a reactor effluent comprising linear alpha-olefins including 1-butene, solvent, unconsumed ethylene dissolved in the reactor effluent, and catalyst composition from the reactor, d) separating ethylene and 1-butene collectively from the remaining reactor effluent, and e) recycling at least a part of the ethylene and the 1-butene separated in step d) into the reactor.

Abstract: The invention refers to a gas turbine blade including an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord with an axial chord length defined by an axial length of a straight line connecting the leading edge and trailing edge of the airfoil depending on the span. The axial chord length increases at least from 80% span to 100% span.

Abstract: The present invention relates to a method for preparing linear alpha-olefins (LAO) by oligomerization of ethylene in the presence of solvent and homogenous catalyst, comprising the steps of: (i) feeding ethylene, solvent and catalyst into an oligomerization reactor, (ii) oligomerizing the ethylene in the reactor, (iii) removing a reactor outlet stream comprising solvent, linear alpha-olefins, ethylene, and catalyst from the reactor via a reactor outlet piping system, (iv) transferring the reactor outlet stream to a catalyst deactivation and removal step, and (v) deactivating and removing the catalyst from the reactor outlet stream, characterized in that at least one organic amine is added into the oligomerization reactor and/or into the reactor outlet piping system.

Abstract: A process for preparing a catalyst provided in the form of a metal oxide catalyst having at least one element selected from Mo, Te, Nb, V, Cr, Dy, Ga, Sb, Ni, Co, Pt and Ce. The catalyst is subjected to an aftertreatment to increase the proportion of the M1 phase, by contacting the catalyst with steam at a pressure below 100 bar or by contacting the catalyst with oxygen to obtain an aftertreated catalyst. The aftertreated catalyst may be used for oxidative dehydrogenation processes.

Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.

Abstract: The invention refers to a gas turbine blade including an airfoil extending in radial direction from a blade root to a blade tip, defining a span ranging from 0% at the blade root to 100% at the blade tip, and extending in axial direction from a leading edge to a trailing edge, which limit a chord with an axial chord length defined by an axial length of a straight line connecting the leading edge and trailing edge of the airfoil depending on the span. The axial chord length increases at least from 80% span to 100% span.

Abstract: The present invention relates to a method for oligomerization of ethylene, comprising the steps: a) feeding ethylene, solvent and a catalyst composition comprising catalyst and cocatalyst into a reactor, b) oligomerizing ethylene in the reactor, c) discharging a reactor effluent comprising linear alpha-olefins including 1-butene, solvent, unconsumed ethylene dissolved in the reactor effluent, and catalyst composition from the reactor, d) separating ethylene and 1-butene collectively from the remaining reactor effluent, and e) recycling at least a part of the ethylene and the 1-butene separated in step d) into the reactor.

Abstract: An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.

Abstract: A gas turbine is disclosed which includes an annular combustion chamber defined by an inner wall and an outer wall. A stator airfoil row can be defined by an annular inner stator wall and an annular outer stator wall housing a plurality of stator airfoils, and at least a rotor airfoil row defined by an annular inner rotor wall and an annular outer rotor wall housing a plurality of rotor airfoils. A gap is arranged, for example, between at least one of the inner stator wall and the inner combustion chamber wall, and the outer stator wall and the outer combustion chamber wall, upstream of said stator airfoil row. A border of at least one of the inner and outer stator wall facing the gap can be axisymmetric.

Abstract: The invention relates to a method and a device for generating hydrogen (5), wherein an input (1) comprising carbon is fed longitudinally through a tube-shaped reaction chamber (Z), together with water steam (2), and is thereby converted by steam reforming, and hydrogen (4) formed during steam reforming is continuously drawn off out of the reaction chamber (Z) through a separating wall (T), said wall being selectively hydrogen-permeable at least in segments, and at a pressure less than the pressure in the reaction chamber (Z) and greater than the ambient pressure, having greater purity than product (5), characterized in that a separating wall (T) is used, the selectively hydrogen-permeability segments thereof being disposed such that a hydrogen partial pressure drop exists over the entire surface of each of such segments between the reaction chamber side and the hydrogen extraction side (W).

Abstract: A method and device for the catalytic decomposition of laughing gas in a laughing-gas-bearing gas. The method includes diluting the laughing-gas-bearing gas with a diluting gas, while forming a laughing-gas-bearing charge gas. The laughing-gas bearing charge gas is passed through a heat-exchange step where heat exchange occurs with an exhaust. A heating step occurs for occasional heating of the laughing-gas-bearing charge gas in a fixed-bed reactor for catalytic decomposition of the laughing gas. In some embodiments the diluting gas is dried, and at least a part of the exhaust from the catalytic decomposition of the laughing gas is mixed with the laughing-gas-bearing charge gas upstream of the catalytic decomposition of the laughing gas.