A gate-insulated thin film transistor is disclosed. One improvement is that the thin film transistor is formed on a substrate through a blocking layer in between so that it is possible to prevent the transistor from being contaminated with impurities such as alkali ions which exist in the substrate. Also, a halogen is added to either or both of the blocking layer and a gate insulator of the transistor in order that impurities such as alkaline ions, dangling bonds and the like can be neutralized, therefore, the reliability of the device is improved.

Thin-film transistor

A modulated flow transfer apparatus for transferring a fluid flow from a static element to a rotor of a gas turbine engine has an annular static inducer for accelerating the fluid flow in a substantially circumferential direction. The inducer has an annular row of identical first and second flow passages with first and second inlets respectively and outlets. First and second flow means direct first and second portions of the flow to the first and second flow passages, respectively. A valve is used for selectively modulating the second portion of the flow which together with a controller may be used for selectively preventing the second portion of flow from flowing through the second flow passages during a first cruise of engine operation and allowing substantially unrestricted flow therethrough during a takeoff mode of engine operation. The second flow means preferably includes an inducer manifold disposed between the valve and the second inlets. Exhaust ducts connect corresponding ones of the second inlets to the inducer manifold. The inducer manifold is preferably disposed inside a plenum used to feed cooling air to the first passages.

Modulated turbine cooling system

A first-stage nozzle vane includes an airfoil having a profile according to Table I. The annulus profile of the hot gas path is defined in conjunction with the airfoil profile and the profile of the inner and outer walls by the Cartesian coordinate values given in Tables I and II, respectively. The airfoil is a three-dimensional bowed design, both in the airfoil body and in the trailing edge. The airfoil is steam and air-cooled by flowing cooling mediums through cavities extending in the vane between inner and outer walls.

Airfoil shape for a turbine nozzle

Convective cooling of turbine hot parts using a closed loop system is disclosed. Preferably, the present invention is applied to cooling the hot parts of combustion turbine power plants, and the cooling provided permits an increase in the inlet temperature and the concomitant benefits of increased efficiency and output. In preferred embodiments, methods and apparatus are disclosed wherein air is removed from the combustion turbine compressor (22, 26) and delivered to passages internal to one or more of a combustor and turbine hot parts (100). The air cools the combustor and turbine hot parts via convection and heat is transferred through the surfaces of the combustor and turbine hot parts.

Closed loop air cooling system for combustion turbines

A compressor airfoil (12) includes pressure and suction sides (18,20) extending from root (22) to tip (24) and between leading and trailing edges (26,28). Transverse sections have respective chords and camber lines. Centers of gravity (34) of the sections are aligned along a double bowed stacking axis for improving performance.

Double bowed compressor airfoil

A turbine cooling supply circuit for a gas turbine engine is disclosed in which the flow of coolant through the engine is directed to minimize temperature rise prior to discharge into the turbine. Bleed air from an impeller stage of a compressor is channeled along a backwall thereof into a cavity disposed radially inwardly of a combustor casing. The cavity is divided by a lightweight tubular member having a circumferentially uniform contour into a non-flow zone proximate the casing and a flow zone proximate a rotor. Maintenance of a high tangential flow component in the bleed flow in the flow zone facilitates discharge of the flow through apertures in a rotor into a bore portion thereof, minimizing work input and temperature rise of the coolant. Further, the coolant is isolated from the hot casing wall and nonuniform structures disposed thereon, thereby reducing heat flux and temperature rise associated with aerodynamic drag caused by increased surface area, nonuniform interruptions in the stationary surface or any combination thereof. Features are incorporated in the tubular member to provide margin against buckling.

Gas turbine engine cooling supply circuit

The invention comprises a blade for a gas turbine engine including an airfoil portion having a non-linear stacking axis intersecting a reference radial axis that is effective for generating a compressive component of bending stress due to centrifugal force acting on the blade. The compressive component of bending stress is provided in a life-limiting section of the blade, which, for example, includes trailing and leading edges of the blade. Inasmuch as the stacking axis, which represents the locus of centers of gravity of transverse sections of an airfoil portion of the blade, is non-linear, an increased amount of a compressive, component of bending stress can be generated at a life-limiting section between a root and tip of the blade without substantially increasing bending stress at the root of the blade due to the non-linear stacking.

John J. Bourneuf

Papers

Gas turbine engine cooling supply circuit

Gas turbine engine blade