GAS TURBINE ENGINES WITH IMPROVED AIRFOIL DUST REMOVAL
First Claim
1. An airfoil for a rotor blade in a gas turbine engine, comprising:
- a first side wall;
a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform;
a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip; and
an internal cooling system arranged within the first and second side walls configured to direct cooling air from one or more source passages, through the airfoil, and out of the airfoil,wherein the internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit, the internal cooling system further including tip slots formed in the blade tip and trailing edge slots formed in the trailing edge, andwherein the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit are formed by a plurality of internal passages fluidly coupled to the one or more source passages, and wherein each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.
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Accused Products
Abstract
An airfoil for a rotor blade in a gas turbine engine includes a first side wall and a second side wall joined to the first side wall at a leading edge and a trailing edge. The airfoil further includes a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip and an internal cooling system. The internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit. Each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis.
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Citations
20 Claims
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1. An airfoil for a rotor blade in a gas turbine engine, comprising:
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a first side wall; a second side wall joined to the first side wall at a leading edge and a trailing edge, the first and second side walls extending in a radial outward direction from a base coupled to an airfoil platform; a tip cap extending between the first and second side walls such that the tip cap and at least portions of the first and second side walls form a blade tip; and an internal cooling system arranged within the first and second side walls configured to direct cooling air from one or more source passages, through the airfoil, and out of the airfoil, wherein the internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit, the internal cooling system further including tip slots formed in the blade tip and trailing edge slots formed in the trailing edge, and wherein the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit are formed by a plurality of internal passages fluidly coupled to the one or more source passages, and wherein each of the internal passages within the leading edge cooling circuit, the central cooling circuit, and the trailing edge cooling circuit is bounded in the radial outward direction with a surface that has at least one escape hole or that is positively angled in the radial outward direction relative to a chordwise axis. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
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16. A method for producing an airfoil of a rotor blade for a gas turbine engine, comprising the steps of:
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providing a baseline airfoil with an internal cooling system defined by internal walls configured to direct cooling air from one or more source passages, through the airfoil, and out of the airfoil, wherein the internal cooling system includes a leading edge cooling circuit, a central cooling circuit, and a trailing edge cooling circuit; evaluating the internal walls and identifying stagnation areas; providing a modified airfoil from the baseline airfoil by adding escape holes within the internal walls in the stagnation areas; and producing the modified airfoil. - View Dependent Claims (17, 18, 19, 20)
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Specification