Turbine vane airfoil profile
AssigneePratt & Whitney Canada Corp.
InventorsMohammed Ennacer, Panagiota Tsifourdaris, Remo Marini, Niloofar Moradi, Daniel Lecuyer, Patricia Phutthavong, Farzad Ashrafi
Life of this patent
Estimating the term…
Abstract
A turbine vane for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface. The surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.
Claims20
A turbine vane for a gas turbine engine, the turbine vane comprising:
- an airfoil having a leading and a trailing edge joined by a pressure and a suction side to provide an external airfoil surface;
- and
- wherein the external airfoil surface is formed in substantial conformance with cross-section profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading edge and the trailing edge at the span location.
A high pressure turbine vane comprising:
- an airfoil having an external airfoil surface formed in substantial conformance with cross-section airfoil profiles defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein.
A gas turbine engine comprising:
- a high pressure turbine configured to drive a high pressure compressor;
- wherein the high pressure turbine comprises at least one stage of turbine vanes, wherein at least one of the turbine vanes of the at least one stage comprises an airfoil having leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface;
- and
- wherein the external airfoil surface is formed in substantial conformance with cross-section profiles of the airfoil defined by a set of Cartesian coordinates set forth in Table 1 and incorporated by reference herein, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
Dependencies are inferred from the claim text.