Method of fabricating integrally bladed rotor and stator vane assembly
First Claim
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1. A method of fabricating an integrally bladed rotor of a gas turbine engine, the integrally bladed rotor including a disc with an array of blades affixed to the disc, the blades extending radially outwardly and being circumferentially spaced apart, the method comprising:
- a) operating a milling machine to cut a blank of the integrally bladed rotor secured in a device for ensuring a machining position, thereby forming the integrally bladed rotor having the blades extending from the disc;
b) scanning the fabricated integrally bladed rotor to generate a complete 3 dimensional profile of the integrally bladed rotor before removing the integrally bladed rotor from the device;
c) calculating a center of gravity of the integrally bladed rotor based on the complete 3-dimensional profile of the integrally bladed rotor, and verifying whether or not the center of gravity is within an acceptable range with respect to a reference point of the integrally bladed rotor; and
thend) removing the integrally bladed rotor from the device if the verification has a positive result.
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Abstract
A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced.
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6 Claims
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1. A method of fabricating an integrally bladed rotor of a gas turbine engine, the integrally bladed rotor including a disc with an array of blades affixed to the disc, the blades extending radially outwardly and being circumferentially spaced apart, the method comprising:
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a) operating a milling machine to cut a blank of the integrally bladed rotor secured in a device for ensuring a machining position, thereby forming the integrally bladed rotor having the blades extending from the disc; b) scanning the fabricated integrally bladed rotor to generate a complete 3 dimensional profile of the integrally bladed rotor before removing the integrally bladed rotor from the device; c) calculating a center of gravity of the integrally bladed rotor based on the complete 3-dimensional profile of the integrally bladed rotor, and verifying whether or not the center of gravity is within an acceptable range with respect to a reference point of the integrally bladed rotor; and
thend) removing the integrally bladed rotor from the device if the verification has a positive result. - View Dependent Claims (2, 3)
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4. A method of fabricating a stator vane assembly of a gas turbine engine, the stator vane assembly including coaxial inner and outer rings with an array of stator vanes circumferentially spaced apart and radially extending between the inner and outer rings, the method comprising:
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a) electronically scanning each of the stator vanes to capture geometric data representative of a 3 dimensional profile of the individual stator vanes before the stator vanes are welded to the respective inner and outer rings; b) determining a stator vane array pattern between the inner and outer rings of the assembly to be fabricated, using the geometric data of the individual stator vanes in a computing process, the determined stator vane array pattern having openings between trailing edges of the stator vanes adapted to uniformly direct fluid flow; and c) positioning and welding the respective stator vanes between the inner and outer rings in accordance with the determined stator vane array pattern. - View Dependent Claims (5, 6)
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Specification