Abstract: A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (11) and a pressure side (10), and a platform (4), and at least one second row of turbine blades or vanes (2), which are arranged upstream of the first row of turbine blades or vanes (1) in the direction of the hot gases (12), and in the axial direction of the rotor and likewise have a platform (4). There is at least one seal (5, 6), through which a cooling air leakage stream (7) emerges while the gas turbine is operating, between the first row of turbine blades or vanes (1) and the second row of turbine blades or vanes (2), in the region of the respective platforms (4). An element guides the leakage stream (7) of cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades or vanes (1).

Abstract: A gas turbine arrangement includes a rotor, a hot-gas passage, through which a hot-gas stream (12) flows while the gas turbine is operating, at least one first row of turbine blades or vanes (1), which have an airfoil(3) with a suction side (11) and a pressure side (10), and a platform (4), and at least one second row of turbine blades or vanes (2), which are arranged upstream of the first row of turbine blades or vanes (1) in the direction of the hot gases (12), and in the axial direction of the rotor and likewise have a platform (4). There is at least one seal (5, 6), through which a cooling air leakage stream (7) emerges while the gas turbine is operating, between the first row of turbine blades or vanes (1) and the second row of turbine blades or vanes (2), in the region of the respective platforms (4). An element guides the leakage stream (7) of cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades or vanes (1).

Abstract: Air and gaseous fuel for a gas turbine combustor are mixed within a nozzle prior to being introduced into the combustor. The fuel is introduced into an upstream end of an elongated passageway through the nozzle, while air entry ports are located in the throat of a venturi section at an intermediate portion of the elongated passageway. Each of the air passageways leading to the air entry ports is inclined at an acute angle to the longitudinal axis of the elongated passageway so that the direction of flow of air through the respective air passageway into the venturi section and the direction of fuel flow through the elongated passageway are both towards the downstream section of the elongated passageway. The venturi section allows mixing of low pressure air and high pressure gaseous fuel without excessive fuel pressure loss. Water can be injected into a mixing chamber downstream of the venturi section and upstream of nozzle outlet ports.

Abstract: Air and gaseous fuel for a gas turbine combustor are mixed within a nozzle prior to being introduced into the combustor. The fuel is introduced into an upstream end of an elongated passageway through the nozzle, while air entry ports are located in the throat of a venturi section at an intermediate portion of the elongated passageway. Each of the air passageways leading to the air entry ports is inclined at an acute angle to the longitudinal axis of the elongated passageway so that the direction of flow of air through the respective air passageway into the venturi section and the direction of fuel flow through the elongated passageway are both towards the downstream section of the elongated passageway. The venturi section allows mixing of low pressure air and high pressure gaseous fuel without excessive fuel pressure loss. Water can be injected into a mixing chamber downstream of the venturi section and upstream of nozzle outlet ports.

Abstract: A thermal shielding apparatus for use in the low pressure stage of a turbine engine having a plurality of tubular honeycomb cells which are axially aligned and arranged perpendicularly to a radially outwardly directed heat flux. The cells are layered and are housed by an inner and outer liner. The outer liner and an outer casing form a space between them, the outer casing being located radially outward from the outer liner. The layers of honeycomb cells reduce radiant heat flow to the outer casing.