MANUFACTURING PROCESS OF A LIGHTENED TURBOMACHINE BLADE

• US 20150226068A1
• Filed: 10/30/2013
• Published: 08/13/2015
• Est. Priority Date: 10/30/2012
• Status: Abandoned Application

• Current Assignee: Pietro Rosa Tbm Sri
• Original Assignee: Pietro Rosa Tbm Sri
• Inventors: Maurizio, Andrea
• Application Number:
  US14/067,435
• Publication Number:
  US 20150226068A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B23P 15/02 turbine or like blades from one piece
• CPC Class Codes: B23P 15/04 turbine or like blades from several pieces
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F04D 29/023 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/384 characterised by form
• CPC Class Codes: F05D 2220/36 specially adapted for the fan of turbofan engines
• CPC Class Codes: F05D 2230/23 by permanently joining parts together
• CPC Class Codes: F05D 2230/232 by welding
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49339 Hollow blade

Abstract

A manufacturing process of a lightened blade for turbomachines, comprising the steps of manufacturing a semi-finished product provided with an oblong plate-like portion whose shape substantially approximates the shape of the main airfoil-shaped body of the shaped airfoil of the lightened blade to be built; obtaining, substantially at the centre of one of the two faces of said plate-like portion, at least one hollow seat of predetermined shape; positioning in abutment on the surface of the face of the plate-like portion where the hollow seat is, a covering plate, the dimensions of which exceed those of the hollow seat, so as to cover the surface of the face of the plate-like portion where the hollow seat is, up to the larger lateral edges of the same plate-like portion; fixing in a rigid and unmovable way the covering plate on the face of the plate-like portion by means of an adhesive layer or lap welding that affects the perimeter strip or flap of the covering plate that rests directly on the surface of the face of the plate-like portion, outside the hollow seat; and finally, stripping/removing, by means of mechanical machining with material removal, the excess material from the resulting work piece, so as to obtain the shaped airfoil of the lightened blade.

Claims

1. A manufacturing process of a lightened turbomachine blade (1) comprising the steps of

obtaining a semi-finished product (100) provided with an oblong plate-like portion (101), the shape of which substantially approximates the shape of the main airfoil-shaped body (5) of the shaped airfoil (3) of the lightened blade (1) to be built;

and

obtaining, substantially at the centre of one of the two faces of said plate-like portion (101), at least one hollow seat (101a) of predetermined shape;

the construction method being characterised by additionally comprising also the steps of

positioning in abutment on the surface of the face of the plate-like portion (101) where said hollow seat (101a) is located, above said hollow seat (101a), a covering plate (103) which is dimensioned so as to cover the surface of the face of the plate-like portion (101) where said hollow seat (101a) is located, up to the larger lateral edges of the oblong plate-like portion (101), so as to completely cover the hollow seat (101a) while remaining outside said hollow seat (101a);

fixing in a rigid and unmovable way the covering plate (103) on the face of the plate-like portion (101) by means of an adhesive layer or lap welding (7) that affects the perimeter strip or flap of the covering plate (103) that rests directly on the surface of the face of the plate-like portion (101), outside the hollow seat (101a); and

finally

stripping/removing, by means of mechanical machining with material removal, the excess material from the covering plate (103) and the plate-like portion (101) which is located at the larger lateral edges of the plate-like portion (101), so as to realize the leading (3a) and the trailing edges (3b) of the shaped airfoil (3), thus to obtain the shaped airfoil (3) of the lightened plate (1).

2. Manufacturing process of a lightened blade according to claim 1, characterised in that the covering plate (103) is dimensioned so as to substantially cover the whole surface of the face of the oblong plate-like portion (101) where the hollow seat (101a) is located.

3. Manufacturing process of a lightened blade according to claim 1, characterized by also comprising the step of obtaining, on the face of the plate-like portion (101) which houses said hollow seat (101a), a perimeter annular groove (101b) surrounding said hollow seat (101a).

4. Manufacturing process of a lightened blade according to claim 3, characterized in that the perimeter annular groove (101b) surrounds the hollow seat (101a) without interruption.

5. Manufacturing process of a lightened blade according to claim 4, characterized in that the perimeter annular groove (101b) surrounds the hollow seat (101a) while remaining at a predetermined minimum distance from the perimeter edge of the hollow seat (101a).

6. Manufacturing process of a lightened blade according to claim 3, characterized in that the covering plate (103) is fixed on the face of the plate-like portion (101) by lap welding or overlapping bonding (7) that affects the perimeter strip or flap of the covering plate (103) that rests directly on surface of the face of the plate-like portion (101), outside the perimeter annular groove (101b).

7. Manufacturing process of a lightened blade according to claim 1, characterized in that the step of stripping/removing the excess material from the resulting work piece comprises the step of stripping/removing, by means of mechanical machining with material removal, the flaps of the covering plate (103) which cantilever projecting from the surface of the face of the plate-like portion (101).

8. Manufacturing process of a lightened blade according to claim 1, characterized in that the semi-finished product (100) also comprises a squat lower portion (102) whose shape approximates the shape of the coupling shank (2) of the lightened blade (1), and that the step of stripping/removing the excess material from the resulting work piece comprises the step of stripping/removing, by means of mechanical machining with material removal, any excess material localized on the squat lower portion (102) so as to obtain the coupling shank (2) of the lightened blade (1).

9. Manufacturing process of a lightened blade according to claim 1, characterized in that the hollow seat (101a) on the face of said oblong plate-like portion (101) has an extension exceeding 40% of the total surface of the same face of the plate-like portion (101).

10. Manufacturing process of a lightened blade according to claim 1, characterized in that the shape of the hollow seat (101a) substantially copies on a reduced scale the three-dimensional shape of the shaped airfoil (3) to be realised.

11. Manufacturing process of a lightened blade according to claim 1, characterized in that the layer of adhesive or the lap welding (7) extends without interruption along the entire perimeter strip or flap of the covering plate (103) that rests directly on surface of the face of the plate-like portion (101), outside the hollow seat (101a).

12. A lightened turbomachine blade (1) of the type comprising at least one coupling shank (2) and a shaped airfoil (3) which is rigidly coupled/connected with said coupling shank (2) and is internally provided with a large weight-reducing recess (4);

said shaped airfoil (3) being formed of a main airfoil-shaped body (5) which presents, substantially at the centre of one of the two faces, at least one hollow seat (5a) of predetermined shape; and

a cover plate (6) which covers the face of the airfoil-shaped body (5) where the hollow seat (5a) is located, so as to close said hollow seat (5a) obtaining the weight-reducing recess (4), and is immovably fixed on the face of the airfoil-shaped body (5) by means of an adhesive layer or a lap weld that affects the perimeter strip or flap (6a) of the cover (6) that rests directly on the surface of the face of the main airfoil-shaped body (5), outside the hollow seat (5a);

said blade being characterised in that the cover plate (6) is dimensioned so as to extend on surface of the face of the main airfoil-shaped body (5) which houses the hollow seat (5a), up to reach both larger lateral edges of the main airfoil-shaped body (5), so as also to form part of the leading edge (3a) and the trailing edge (3b) of the shaped airfoil (3) of the lightened blade (1).

13. Lightened blade according to claim 12, characterized in that the main airfoil-shaped body (5) is also provided with a perimeter annular groove (5b) that substantially surrounds the hollow seat (5a), and in that the adhesive layer or the lap weld affects the perimeter portion of the face of the main airfoil-shaped body (5) that is located outside the annular groove (5b).

14. Lightened blade according to claim 12, characterised in that said hollow seat (5a) has an extension exceeding 40% of the total surface of the face of the main airfoil-shaped body (5) where the hollow seat (5a) is.

15. Lightened blade according to claim 12, characterized in that said main airfoil-shaped body (5) is made in one piece with said coupling shank (2).