Turbine blades with tip portions having converging cooling holes
First Claim
1. A turbine rotor blade for a turbine section of an engine, the turbine section including a shroud surrounding the turbine rotor blade, comprising:
- a platform; and
an airfoil extending from the platform into a mainstream gas path of the turbine section, the airfoil comprisinga pressure side wall;
a suction side wall joined to the pressure side wall at a leading edge and a trailing edge;
a tip cap extending between the suction side wall and the pressure side wall;
a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges from an inlet to an outlet, wherein the first squealer tip extension terminates at a radial wall, and wherein the outlet of the first cooling hole is formed on the radial wall,wherein the first squealer tip extension includes a forward surface that is continuous with a forward surface of the pressure side wall and is completely forward of the forward surface of the pressure side wall relative to a radial axis of the pressure side wall, and wherein the first squealer tip extension further includes a trailing surface that extends in a forward direction at a second angle, non-parallel to the radial axis of the pressure side wall, anda second squealer tip extension extending from the suction side wall at a third angle relative to the suction side wall, wherein the second squealer tip extension includes a trailing surface that is continuous with a trailing surface of the suction side wall and is completely forward of the trailing surface of the suction side wall relative to a radial axis of the suction side wall; and
an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
1 Assignment
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Accused Products
Abstract
A turbine rotor blade is provided with for a turbine section of an engine that includes a shroud surrounding the rotor blade. The rotor blade includes a platform and an airfoil extending from the platform into a mainstream gas path. The airfoil includes a pressure side wall, a suction side wall joined to the pressure side wall at a leading edge and a trailing edge, a tip cap extending between the suction side wall and the pressure side wall, a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges between an inlet and an outlet; an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole.
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Citations
17 Claims
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1. A turbine rotor blade for a turbine section of an engine, the turbine section including a shroud surrounding the turbine rotor blade, comprising:
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a platform; and an airfoil extending from the platform into a mainstream gas path of the turbine section, the airfoil comprising a pressure side wall; a suction side wall joined to the pressure side wall at a leading edge and a trailing edge; a tip cap extending between the suction side wall and the pressure side wall; a first squealer tip extension extending from the pressure side wall at a first angle relative to the pressure side wall, the first squealer tip extension defining a first cooling hole that converges from an inlet to an outlet, wherein the first squealer tip extension terminates at a radial wall, and wherein the outlet of the first cooling hole is formed on the radial wall, wherein the first squealer tip extension includes a forward surface that is continuous with a forward surface of the pressure side wall and is completely forward of the forward surface of the pressure side wall relative to a radial axis of the pressure side wall, and wherein the first squealer tip extension further includes a trailing surface that extends in a forward direction at a second angle, non-parallel to the radial axis of the pressure side wall, and a second squealer tip extension extending from the suction side wall at a third angle relative to the suction side wall, wherein the second squealer tip extension includes a trailing surface that is continuous with a trailing surface of the suction side wall and is completely forward of the trailing surface of the suction side wall relative to a radial axis of the suction side wall; and an internal cooling circuit configured to deliver cooling air to a gap between the pressure side squealer tip extension and the shroud via the first cooling hole. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A turbine section of a gas turbine engine, comprising:
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a shroud; and a rotor assembly with a turbine rotor blade comprising a platform defining a mainstream gas path; and an airfoil extending from the platform into the mainstream gas path;
the airfoil comprisinga pressure side wall; a suction side wall joined to the pressure side wall at a leading edge and a trailing edge; a tip cap extending between the suction side wall and the pressure side wall; a first squealer tip extension extending from the pressure side wall to define a gap between the rotor assembly and the shroud, the first squealer tip extension extending at a first angle relative to the pressure side wall and defining a first cooling hole that converges from an inlet to an outlet, wherein the first squealer tip extension terminates at a radial wall, and wherein the outlet of the first cooling hole is formed on the radial wall, wherein the first squealer tip extension includes a forward surface that is continuous with a forward surface of the pressure side wall and is completely forward of the forward surface of the pressure side wall relative to a radial axis of the pressure side wall, and wherein the first squealer tip extension further includes a trailing surface that extends in a forward direction at a second angle, non-parallel to the radial axis of the pressure side wall, and a second squealer tip extension extending from the suction side wall at a third angle relative to the suction side wall, wherein the second squealer tip extension includes a trailing surface that is continuous with a trailing surface of the suction side wall and is completely forward of the trailing surface of the suction side wall relative to a radial axis of the suction side wall; and an internal cooling circuit configured to deliver cooling air to the gap between the pressure side squealer tip extension and the shroud via the first cooling hole. - View Dependent Claims (13, 14, 15, 16, 17)
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Specification