|
|
Found results for
 patents
1.
|
Method for calculating the thickness of the trailing and leading edges on a blade profile
| Application Number |
17634716 |
| Grant Number |
12005666 |
| Status |
In Force |
| Filing Date |
2020-08-07 |
| First Publication Date |
2022-09-08 |
| Grant Date |
2024-06-11 |
| Owner |
- SAFRAN AERO COMPOSITE (France)
- SAFRAN AIRCRAFT ENGINES (France)
- SAFRAN AEROSPACE COMPOSITES (USA)
|
| Inventor |
- Le Cloarec, Damien Vincent
- Giacovelli, Clement
- Sherman, Jeffrey Steven
- Thomas, Mickaelle Lucie Alicia
|
Abstract
A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.
IPC Classes ?
- B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
- B29D 99/00 - Subject matter not provided for in other groups of this subclass
- G05D 5/02 - Control of dimensions of material of thickness, e.g. of rolled material
- F01D 5/14 - Form or construction
|
2.
|
METHOD FOR CALCULATING THE THICKNESS OF THE TRAILING AND LEADING EDGES ON A BLADE PROFILE
| Application Number |
FR2020051450 |
| Publication Number |
2021/028637 |
| Status |
In Force |
| Filing Date |
2020-08-07 |
| Publication Date |
2021-02-18 |
| Owner |
- SAFRAN AERO COMPOSITE (France)
- SAFRAN AIRCRAFT ENGINES (France)
- SAFRAN AEROSPACE COMPOSITES (USA)
|
| Inventor |
- Le Cloarec, Damien, Vincent
- Giacovelli, Clément
- Sherman, Jeffrey, Steven
- Thomas, Mickaëlle, Lucie, Alicia
|
Abstract
The invention relates to a method (500) for verifying the conformity of the aerodynamic profile of an actual blade of an aircraft turbine engine with respect to a theoretical blade, which comprises: - constructing (521) a skeleton curve of the theoretical blade and constructing a skeleton curve of the actual blade, - constructing (522) a thickness law of the theoretical blade and constructing a thickness law of the actual blade, the thickness law of a blade corresponding to the curve of the thickness of the blade as a function of the curvilinear length of the skeleton curve from a leading edge of the blade to a trailing edge of the blade, the thickness being the dimension of the blade that extends perpendicular to the skeleton curve at each point of the skeleton curve, - superimposing (523) the thickness law of the actual blade on the thickness law of the theoretical blade, and - extracting (524) the leading and trailing edge thicknesses.
IPC Classes ?
- F01D 5/14 - Form or construction
- G01B 11/24 - Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
- G01B 21/20 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring contours or curvatures, e.g. determining profile
|
|
