The present invention provides a gas turbine combustor that has a fuel injection nozzle using a fluid other than liquid fuel to atomize the liquid fuel and that can suppress a reduction in power generation efficiency resulting from a heat loss while promoting the atomization of the liquid fuel. The gas turbine combustor is adapted to mix liquid fuel with combustion air led from a compressor, burn the mixture, and supply combustion gas generated to a gas turbine. The gas turbine combustor includes a fuel injection nozzle that atomizes the liquid fuel into fine liquid droplets. The fuel injection nozzle includes a first system adapted to supply the liquid fuel and a second system adapted to supply a fluid for atomizing the liquid fuel. Low-boiling liquid fuel is supplied to the second system as the fluid. The second system is adapted to heat and supply the low-boiling liquid fuel.

Gas turbine combustor

System, devices and methods are presented that integrate stretchable or flexible circuitry, including arrays of active devices for enhanced sensing, diagnostic, and therapeutic capabilities. The invention enables conformal sensing contact with tissues of interest, such as the inner wall of a lumen, a the brain, or the surface of the heart. Such direct, conformal contact increases accuracy of measurement and delivery of therapy. Further, the invention enables the incorporation of both sensing and therapeutic devices on the same substrate allowing for faster treatment of diseased tissue and fewer devices to perform the same procedure.

Systems,methods, and devices having stretchable integrated circuitry for sensing and delivering therapy

A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of circular ring turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween including a plurality of axial channels (C) extending over a portion of an aft end portion of the liner parallel to each other, the cross-sectional area of each channel either constant or varying along the length of the channel, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.

Method and apparatus for cooling combustor liner and transition piece of a gas turbine

A system, device and method are presented for utilizing stretchable active integrated circuits with inflatable bodies. The invention allows for such operative features to come into direct contact with body structures, such as the inner wall of a lumen. Such direct contact increases accuracy of measurement and delivery of therapy.

Catheter balloon having stretchable integrated circuitry and sensor array

An array substrate (10) is provided with a pixel electrode (3) disposed in a region defined by two adjacent gate wirings (1) and two adjacent source wirings (2), a switching element (5) for switching a voltage applied to the pixel electrode (3) from the source wiring (2) based on a signal voltage supplied from the gate wiring (1), a common wiring (8) arranged between the two adjacent gate wirings (1) and a common electrode (4) being electrically connected to the common wiring (8) and generating an electric field between the pixel electrode (3) whereto a voltage is applied, wherein the pixel electrode (1) comprises a first pixel electrode (1a) and a second pixel electrode (2a), and the opposing electrode (2) comprises a first opposing electrode (1b) and a second opposing electrode (2b), wherein a first region generates an electric field between the first pixel electrode (1a) and the first opposing electrode (2a) whose light transmittance is lower than that of the first pixel electrode (1a) and a second region generates an electric field between the second pixel electrode (1b) and the second opposing electrode (2b) whose light transmittance is higher than that of the second pixel electrode (1b) are formed.

Display device and driving method thereof

A turbine blade arrangement includes rotating blades respectively provided with a leg which can be respectively inserted into a groove on the outer circumference of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section which has a lateral platform located in an end area on the side of the disk. At least one part of the platform is joined to the turbine disk by way of a retaining element which is independent from the leg of the blades in order to extend the profiled sections of the rotating blades.

Turbine blade arrangement

The invention relates to a gas turbine blade (1) having a combined convective cooling effected by a meandering cooling channel (21) and having an impact cooling effected via an impact cooling insert (37). The impact cooling insert (37) is arranged inside a first partial section (23) of the meandering cooling channel (21) extending along the front edge (8) of the blade pan. The impact cooling insert (37) tapers along this first partial section (23).

Gas turbine blade

In gas turbines, compressed air is supplied via an air duct to combustion chambers and is heated there. Pressure losses in the air duct should be minimized in order to ensure good overall efficiency. This is achieved by the compressed air flowing with approximately constant velocity in the air duct from the compressor to the inlet into the combustion chamber. This is supported by the effective cross section of the air duct being almost constant over this distance.

Gas turbine with a compressor for air

The invention relates to a device for manufacturing a metallic hollow body ( 1 ) having at least one hollow space ( 3, 5, 17 ) and a wall encompassing the hollow space, comprising an exterior casting mold which has at least one inside core ( 33, 35, 47 ) serving to form the hollow space. The exterior casting mold is separable into at least two exterior members ( 29 A, 29 B) and the inside core ( 33, 35, 47 ) is connected via at least one connecting element ( 53 ), which serves to form a through-opening ( 25 ) in the wall ( 23 ) into the hollow space ( 3, 5, 7 ), with an exterior member ( 29 A, 29 B) of the exterior casting mold.

Method and device for producing a metallic hollow body

The invention relates to a blade (13; 14) for a turbine (10), comprising at least one channel (22) which is delimited by walls (19, 20, 21). An insert (25) which can be subjected to the action of a liquid coolant is inserted into at least one channel (22). According to the invention, at least one of the walls (19; 20) is provided with a number of horizontal ribs (24) which are located between the insert (25) and the wall (19; 20). Said insert (25) is provided with openings (27) through which the liquid coolant passes out of the insert (25) and between the horizontal ribs (24). The liquid coolant is therefore conducted along the wall (19, 20) and guided by the horizontal ribs (24) in order to provide improved convection cooling.

Peter Tiemann

Papers

Turbine blade arrangement

Gas turbine blade

Gas turbine with a compressor for air

Method and device for producing a metallic hollow body

Cooling system for a turbine blade