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US 4,908,782 AGranted
Airfoil inspection method
AssigneeCompressor Components Textron Inc.
InventorsHerbert C. Pekarek, Richard D. Pryatel
Life of this patent
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AssigneeCompressor Components Textron Inc.
InventorsHerbert C. Pekarek, Richard D. Pryatel
Estimating the term…
An improved inspection method determines how closely the cross sectional configuration of an airfoil corresponds to a reference cross sectional configuration. When an airfoil is to be inspected, the airfoil is measured and the mean camber line is determined. The mean camber lines of the reference and measured airfoils are shifted relative to each other through a plurality of relationships. A best fit relationship is determined in which the measured and reference airfoils overlie each other to a maximum extent possible. The best fit relationship can be determined by comparing points on the major side surfaces of the measured and reference airfoils. Alternatively, the best fit relationship can be determined by comparing points on the mean camber lines of the measured and reference airfoils.
A method of determining how closely the cross sectional configuration of an airfoil corresponds to a reference cross sectional configuration, said method comprising the steps of measuring the airfoil in a plane extending transversely to a central axis of the airfoil, determining data representative of the mean camber line of the measured airfoil, establishing an initial relationship between the data representative of the measured airfoil mean camber line with data representative of a mean camber line for a reference airfoil, changing the relationship between the data representative of the measured airfoil mean camber line and the data representative of the reference airfoil mean camber line from the initial relationship to each of a plurality of different relationships, and determining at which of the relationships between the data representative of the measured airfoil mean camber line and the data representative of the reference airfoil mean camber line there is a best fit condition in which surfaces of the airfoils overlie each other to the maximum extent possible.
A method of determining how closely the cross sectional configuration of a first airfoil corresponds to the cross sectional configuration of a reference airfoil, said method comprising the steps of measuring the first airfoil in a plane extending transversely to a central axis of the first airfoil, determining data representative of a first line having a configuration which is a function of the configuration of major side surfaces on the first airfoil in the measurement plane, determining data representative of a second line having a configuration which is a function of the configuration of major side surfaces of the reference airfoil in a plane corresponding to the measurement plane, establishing an initial relationship between the data representative of the first and second lines, changing the relationship between the data representative of the first and second lines from the initial relationship to each of a plurality of relationships, and determining for which of the relationships there is a minimum deviation between the points on the major side surfaces of the measured airfoil and corresponding points on the major side surfaces of the reference airfoil.
A method of determining how closely the cross sectional configuration of a selected airfoil corresponds to the cross sectional configuration of a reference airfoil, said method comprising the steps of determining data representative of mean camber lines and their leading and trailing ends for the selected and reference airfoils, shifting the data representative of the mean camber lines relative to each other through a plurality of relationships in each of which a leading end of one of the mean camber lines is disposed on the other mean camber line and the trailing end of the other mean camber line is disposed on the one mean camber line, and comparing the relationship between points associated with the selected airfoil with corresponding points associated with the reference airfoil at the initial and each of the plurality of relationships.
Dependencies are inferred from the claim text.