United Technologies Corporation

Rtx Corporation

Jason B Moran

Russell J Bergman

Mohammed Ennacer

Dominic J Mongillo, Jr

Jeffrey T Morton

Christopher Whitfield

Shawn M McMahon

Justin M Aniello

Kristopher K Anderson

Brett Alan Bartling

Christopher Perron

Stephanie Tanner

Johan K Westin

Jr Dominic J Mongillo

A turbine airfoil includes a body that has inner and outer platforms and an airfoil section that extends between the inner and outer platforms. Cooling holes define external breakout points from the body. The external breakout points are located in accordance with Cartesian coordinates of at least points 1 through 11, 193 through 201, and 268 through 275 set forth in Table 1 herein.

Turbine airfoil having cooling hole arrangement

A vane cluster for a gas turbine engine includes an outer diameter platform and an inner diameter platform. A plurality of vanes span from the outer diameter platform to the inner diameter platform. At least one inbound region is defined between a first vane of the plurality of vanes and a second vane of the plurality of vanes. The first vane includes a suction side facing the inbound region. Each of the vanes includes a leading edge core passage and a trailing edge core passage. A plurality of electrical discharge machined (EDM) holes are disposed within at least 0.500 inches (12.7 mm) of a leading edge of the first vane. Each of the EDM holes connect a leading edge core passage of the vane to an exterior surface of the vane.

Turbine vane cluster including enhanced vane cooling

A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. At least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

Turbine airfoil platform segment with film cooling hole arrangement

A turbine airfoil segment includes inner and outer platforms that are joined by at least one airfoil. The airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface. The airfoil includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in one of Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).

Turbine airfoil segment having film cooling hole arrangement

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Wilbraham, MA, United States of America

Jason B Moran