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US 12,523,154 B1Granted
Gas generator turbine blades in gas turbine engines
AssigneesGE Aerospace Poland Sp. z o.o., GE Avio S.r.l.
InventorsPaweł Bernacki, Grzegorz Karpiński, Francesco Bertini
Life of this patent
Estimating the term…
Abstract
A gas generator turbine blade for a gas turbine engine includes a platform and an airfoil. The airfoil extends in a spanwise direction from the platform to a tip. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.
Claims20
A gas generator turbine blade for a gas turbine engine, the gas generator turbine blade comprising:
- an airfoil having a leading edge and a trailing edge joined by a pressure side and a suction side to provide an external airfoil surface configured to extend from a platform of the gas generator turbine blade in a spanwise direction to a tip;
- and
- wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the airfoil described by a set of Cartesian coordinates defined along axial, circumferential, and span axes having an origin at an intersection of the axes, the 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 the local axial chord, and a span location, a zero span location taken at a point where the airfoil meets the platform, 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 gas generator turbine blade for a gas turbine engine, the gas generator turbine blade comprising:
- a platform;
- and
- an airfoil extending in a spanwise direction from the platform to a tip, the airfoil having an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates defined along axial, circumferential, and span axes having an origin at an intersection of the axes, the set of Cartesian coordinates set forth in Table 1.
A gas turbine engine comprising:
- a gas generator turbine blade having an array of airfoils, wherein at least one airfoil of the array of airfoils has a leading edge and a trailing edge that are joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a span direction to a tip;
- and
- wherein the external airfoil surface is formed in conformance with multiple cross-section profiles of the at least one airfoil described by a set of Cartesian coordinates defined along axial, circumferential, and span axes having an origin at an intersection of the axes, the 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 the local axial chord, and a span location, a zero span location taken at a point where the airfoil meets the platform, wherein the local axial chord corresponds to a width of the at least one airfoil between the leading edge and the trailing edge at the span location.
Dependencies are inferred from the claim text.