Abstract: A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2).

Abstract: The present invention is directed to distillation systems and methods. The still may have an impermeable nonporous membrane that may be extruded, molded, vacuum formed or sprayed-on. The membrane may be installed in a lightweight basin as a liner. The distillation system may also include a unique sealing system that may include a gasket with a cross-section shaped like the lowercase letter “e” and may include a trim piece that hold a basin casing and casing cover together. The distillation system may be designed in such a manner so as to make shipping and assembly easy and cost effective. For example, the distillation system may be constructed as a kit that all needed components and all the components are placed inside of a standard dimension box for shipping. In various embodiments, the distillation system may be a solar distillation system.