Adaptive machining of cooled turbine airfoil

Patent metadata

Field	Value
Publication number	US-11414997-B2
Application number	US-201816478004-A
Country	US
Kind code	B2
Filing date	Jan 12, 2018
Priority date	Jan 13, 2017
Publication date	Aug 16, 2022
Grant date	Aug 16, 2022

Abstract

A method is provided for machining an airfoil section (12) of a turbine blade or vane produced by a casting process. The airfoil section (12) has an outer wall (18) delimiting an airfoil interior having one or more internal cooling passages (28). The method involves: receiving design data pertaining to the airfoil section (12), including a nominal outer airfoil form (40N) and nominal wall thickness (TN) data; generating a machining path by determining a target outer airfoil form (40T), the target outer airfoil form (40T) being generated by adapting the nominal outer airfoil form (40N) such that a nominal wall thickness (TN) is maintained at all points on the outer wall around the one or more internal cooling passages (28) in a subsequently machined airfoil section; and machining an outer surface (18a) of the airfoil section (12) produced by the casting process according to the generated machining path, to remove excess material to conform to the generated target outer airfoil form (40T).

First claim

The invention claimed is:

1. A method for machining an airfoil section of a turbine blade or vane produced by a casting process, the airfoil section comprising an outer wall delimiting an airfoil interior having one or more internal cooling passages, the method comprising:
receiving design data pertaining to the airfoil section, including a nominal outer airfoil form and nominal wall thickness data;
generating a machining path by determining a target outer airfoil form, the target outer airfoil form being generated by adapting the nominal outer airfoil form such that a nominal wall thickness is maintained at all points on the outer wall around the one or more internal cooling passages in a subsequently machined airfoil section; and
machining an outer surface of the airfoil section produced by the casting process according to said machining path, to remove excess material to conform to the generated target outer airfoil form,
wherein determining the target outer airfoil form comprises:
measuring a three-dimensional outer form of the airfoil section after the casting process;
obtaining cooling passage position and form measurements for the one or more internal cooling passages in relation to the measured outer form of the cast airfoil section, the cooling passage position and form measurements being carried out by obtaining actual wall thickness measurements at a plurality of points along the outer wall of the cast airfoil section;
constructing points representing nominal wall thickness values around the measured position of the one or more internal cooling passages;
performing a best fit operation to align the nominal outer airfoil form to said points representing nominal wall thickness values; and
generating the target outer airfoil form by adapting the nominal outer airfoil form after the best fit alignment to pass through each of the points representing nominal wall thickness values.

2. The method according to claim 1 , further comprising constraining the target outer airfoil form such that the target outer airfoil form does not extend beyond the measured outer form of the cast airfoil section.

3. The method according to claim 1 , wherein the measurement of a three-dimensional outer form of the airfoil section is performed by tactile coordinate measuring machine probing, or laser scanning or photogrammetry, or combinations thereof.

4. The method according to claim 1 , wherein the actual wall thickness measurements are performed using ultrasound or x-ray or computed tomography or eddy current, or combinations thereof.

5. The method according to claim 4 , wherein the actual wall thickness measurements are performed at various points along the span-wise and chord-wise directions of the cast airfoil section.

6. The method according to claim 1 , wherein the machining path comprises a numerical control (NC) program.

7. The method according to claim 1 , wherein the machining the outer surface of the airfoil section is carried out by a machining process selected from the group consisting of: grinding, milling, electro-chemical machining (ECM) and electrical discharge machining (EDM).

8. A method for manufacturing a row of turbine blades or vanes, comprising:
producing a plurality turbine blades or vanes by a casting process, each blade or vane comprising an airfoil section with one or more internal cooling passages;
machining an outer surface of each airfoil section subsequent to said casting process by a method according to claim 1 , wherein the machining paths used for said machining are generated specific to the airfoil section of each individual blade or vane.

9. A CAD module for generating machining path data for adaptively machining an airfoil section of a turbine blade or vane produced by a casting process, the airfoil section comprising an outer wall delimiting an airfoil interior having one or more internal cooling passages, wherein:
the CAD module is configured to receive design data pertaining to the airfoil section, including a nominal outer airfoil form and nominal wall thickness data;
the CAD module is configured to generate machining path data by determining a target outer airfoil form, wherein the CAD module is configured to generate the target outer airfoil form by adapting the nominal outer airfoil form such that a nominal wall thickness is maintained at all points on the outer wall around the one or more internal cooling passages in a subsequently machined airfoil section;
the CAD module is configured to receive three-dimensional outer form measurement data pertaining to the cast airfoil section;
the CAD module is configured to obtain cooling passage position and form measurements for the one or more internal cooling passages in relation to the measured outer form of the cast airfoil section, the cooling passage position and form measurements being carried out by obtaining actual wall thickness measurements at a plurality of points along the outer wall of the cast airfoil section;
the CAD module is adapted to construct points representing nominal wall thickness values around the measured position of the one or more internal cooling passages;
the CAD module is adapted to perform a best fit operation to align the nominal outer airfoil form to said points representing nominal wall thickness values; and
the CAD module is adapted to generate the target outer airfoil form by adapting the nominal outer airfoil form subsequent to the best fit alignment, to pass through each of the points representing nominal wall thickness values,
wherein the machining path data defines information for machining an outer surface of the airfoil section produced by the casting process, to remove excess material to conform to the generated target outer airfoil form.

10. The CAD module according to claim 9 , further wherein:
the CAD module is configured to constrain the target outer airfoil form such that the target outer airfoil form does not extend beyond the measured outer form of the cast airfoil section.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Eshak Daniel M
• Kamenzky Susanne
• Miller Jr Samuel R
• Vöhringer Daniel

Classifications

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2230/21

  by casting · CPC title

• F05D2230/14

  Micromachining · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F05D2230/18

  Manufacturing tolerances · CPC title