United Technologies Corporation

Eunice Allen-Bradley

Thomas J Praisner

Eric A Grover

Joel H Wagner

Ricardo Trindade

Keshava Basavapatna Kumar

Shankar S Magge

Andrew S Aggarwala

An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.

Airfoil design having localized suction side curvatures

A turbine blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.

Gas turbine engine turbine blade airfoil profile

An airfoil for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body including a leading edge and a trailing edge joined by a pressure side and a suction side spaced apart from the pressure side to provide an external airfoil surface extending in a radial direction from at least one platform. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location, and the Cartesian coordinates in Table 1 have a tolerance relative to the specified coordinates of up to &#xb1;0.050 inches (&#xb1;1.27 mm).

Gas turbine engine airfoil profile

Inefficiencies associated with the formation of horseshoe vortices in a gas turbine engine having a row of radially extending airfoils, are mitigated with an improved flow passage defined by the suction and pressure surface of two adjacent airfoils and endwalls (disposed proximal to the radially inner and outer ends of the airfoils). The flow passage includes a ridge disposed in one of the endwalls adjacent a suction surface of one of the airfoils, the ridge extending longitudinally from a location at or near the maximum circumferential extent of the airfoil suction side to a downstream location proximal to the trailing edge of the suction surface.

Flow passage for gas turbine engine

An airfoil array includes a laterally extending endwallwith a series of airfoils such asorprojecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages. The endwall has a troughtoward a pressure side of the passage and a more elevated profile toward a suction side of the passage for reducing secondary flow losses.

Airfoil array with an endwall depression and components of the array

A blade or vane includes a platformand an airfoilextending from the platform. The airfoil has a pressure surface offset in a first direction Dfrom a part span mean camber line, a suction surface offset in a second direction Dfrom the part span mean camber line, and a basethat is laterally enlarged in the first direction for reducing secondary flow losses.

Blade or vane with a laterally enlarged base

An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow.

Turbine vane airfoil with turning flow and axial/circumferential trailing edge configuration

A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath.

Separation-resistant inlet duct for mid-turbine frames

An airfoil array includes a laterally extending endwallwith a series of airfoils such as, orprojecting from the endwall. The airfoils cooperate with the endwall to define a series of fluid flow passages. The endwall has a humptoward a pressure side of the passage and a less elevated profile toward a suction side of the passage for reducing secondary flow losses.

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East Hartford, CT, United States of America

Eunice Allen-Bradley