Method and device for repairing an aircraft and/or gas turbine component
AssigneeLufthansa Technik AG
InventorsMichael Ernst, Thiemo Ullrich
Life of this patent
Estimating the term…
Abstract
The invention relates to a method for repairing an aircraft or gas turbine component, wherein the method comprises the following automated steps: a) checking the component for cracks by means of an optical measurement method, wherein determined geometry and/or damage data are stored with reference to the component, b) generating an adaptive processing strategy on the basis of the determined geometry and/or damage data in a data processing unit, c) machining the component, d) determining the changed geometry data of the component, e) performing repair welding, f) checking the component for cracks by means of an optical measurement method.
Claims20
A method for repairing an aircraft component or a gas turbine component, comprising:
- (a) checking a component for damage via an optical measurement system, so as to produce damage data, and storing the damage data in a component-specific manner,
- wherein the component is an aircraft component or a gas turbine component;
- (b) generating an adaptive repair strategy based on the damage data,
- wherein generating the adaptive repair strategy comprises processing the damage data via a data processing unit;
- (c) machining the component in accordance with the adaptive repair strategy;
- (d) gathering altered geometric data with respect to the component,
- wherein the altered geometric data with respect to the component is based on how the component was altered by machining the component;
- and
- (e) carrying out repair welding on the component,
- wherein the damage data comprises a plurality of detected individual images,
- wherein the plurality of detected individual images are put together by transformation and registration processes via the data processing unit to form a full image of the component,
- wherein the full image of the component is broken up into a plurality of image portions,
- wherein each image portion of the plurality of image portions is larger than the detected individual images of the plurality of detected individual images, and
- wherein each image portion of the plurality of image portions is individually checked for damage, and structural features and damage of each image portion of the plurality of image portions is individually determined and differentiated on the basis of model parameters.
A method for repairing an aircraft component or a gas turbine component, comprising:
- (a) checking a component for damage via an optical measurement system, so as to produce damage data, and storing the damage data in a component-specific manner,
- wherein the component is an aircraft component or a gas turbine component;
- (b) generating an adaptive repair strategy based on the damage data,
- wherein generating the adaptive repair strategy comprises processing the damage data via a data processing unit;
- (c) machining the component in accordance with the adaptive repair strategy;
- (d) gathering altered geometric data with respect to the component,
- wherein the altered geometric data with respect to the component is based on how the component was altered by machining the component;
- and
- (e) carrying out repair welding on the component,
- wherein the damage data comprises a plurality of detected individual images,
- wherein the plurality of detected individual images are put together by transformation and registration processes via the data processing unit to form a full image of the component, and
- wherein when damage detected in a first detected individual image of the plurality of detected individual images reaches to an edge of the first detected individual image of the plurality of detected individual images, the damage detected in the first detected individual image that reached the edge of the first detected individual image is marked and is taken into account when analyzing a second detected individual image of the plurality of detected individual images that is adjacent to the first detected individual image.
Dependencies are inferred from the claim text.