Systems and methods for airfoil assembly

Patent metadata

Field	Value
Publication number	US-2015190893-A1
Application number	US-201414571399-A
Country	US
Kind code	A1
Filing date	Dec 16, 2014
Priority date	Jan 3, 2014
Publication date	Jul 9, 2015
Grant date	—

Abstract

A method for assembling an airfoil includes pressing a blade body together with at least one of a blade sheath and a blade cover between a plunger and a die base to join the blade body to the blade sheath and/or the blade cover. The method can include transferring heat from the plunger and/or the die base to at least one of the blade body, the blade sheath and the blade cover to cure an adhesive.

First claim

What is claimed is:

1 . A method for assembling an airfoil comprising:
pressing a blade body together with at least one of a blade sheath and a blade cover between a plunger and a die base to join the blade body to at least one of the blade sheath and the blade cover.

2 . A method as recited in claim 1 , further comprising:
transferring heat from at least one of the plunger and the die base to at least one of the blade body, the blade sheath and the blade cover to cure an adhesive.

3 . A method as recited in claim 2 , wherein transferring heat from at least one of the plunger and the die base includes transferring heat through conduction.

4 . A method as recited in claim 2 , further comprising:
applying an adhesive between a broad side of the blade body at least one of the blade cover and the blade sheath; and curing the adhesive with heat transferred from at least one of the plunger and the die base.

5 . A method as recited in claim 2 , further comprising:
applying an adhesive between a leading edge of the blade body at least one of the blade cover and the blade sheath; and curing the adhesive with heat transferred from at least one of the plunger and the die base.

6 . A method as recited in claim 1 , further comprising:
positioning a compliant layer between a broad side of the blade body and the plunger, wherein the compliant layer is configured to substantially equalize the distribution of pressure applied by the plunger across the broad side of the blade body.

7 . A method as recited in claim 1 , further comprising:
positioning a compliant layer between a broad side of the blade body and the die base, wherein the compliant layer is configured to substantially equalize the distribution of pressure across the broad side of the blade body.

8 . A method as recited in claim 1 , further comprising:
positioning the blade body on the die base, wherein the die base opposes the plunger across the blade body along a longitudinal axis.

9 . A method as recited in claim 1 , further comprising:
supporting the blade body and at least one of the blade sheath and the blade cover with the die base while pressing the blade body and at least one of the blade sheath and the blade cover.

10 . A method as recited in claim 1 , further comprising:
applying pressure to a trailing edge side of the blade body in a chord-wise direction with a cam mechanism for full engagement of a leading edge of the blade body within the blade sheath.

11 . A method as recited in claim 1 , wherein pressing the blade body together with at least one of the blade sheath and the blade cover includes moving the plunger along a longitudinal axis toward a broad side of the blade body.

12 . A method as recited in claim 1 , wherein pressing the blade body together with at least one of the blade sheath and the blade cover includes transferring pressure from a plunger surface to a broad side of the blade body in a plane normal to the broad side of the blade body.

13 . A method as recited in claim 1 , further comprising:
constraining the blade body and the blade sheath with a flexible stopper proximate a leading edge of the blade body.

14 . An airfoil produced by a process comprising:
pressing a blade body together with at least one of a blade sheath and a blade cover between a plunger and a die base to join the blade body to at least one of the blade sheath and the blade cover.

15 . An airfoil as recited in claim 14 , wherein the process further comprises:
transferring heat from at least one of the plunger and the die base to at least one of the blade body, the blade sheath and the blade cover to cure an adhesive.

16 . An airfoil as recited in claim 15 , wherein the process further comprises:
applying an adhesive between a broad side of the blade body at least one of the blade cover and the blade sheath; and curing the adhesive with heat transferred from at least one of the plunger and the die base.

17 . An airfoil as recited in claim 15 , wherein the process further comprises:
applying an adhesive between a leading edge of the blade body at least one of the blade cover and the blade sheath; and curing the adhesive with heat transferred from at least one of the plunger and the die base.

18 . An airfoil as recited in claim 14 , wherein the process further comprises:
positioning a compliant layer between a broad side of the blade body and the plunger, wherein the compliant layer is configured to substantially equalize the distribution of pressure applied by the plunger across the broad side of the blade body.

19 . An airfoil as recited in claim 14 , wherein the process further comprises:
positioning a compliant layer between a broad side of the blade body and the die base, wherein the compliant layer is configured to substantially equalize the distribution of pressure across the broad side of the blade body.

20 . An airfoil as recited in claim 14 , wherein the process further comprises:
applying pressure to a trailing edge side of the blade body in a chord-wise direction with a cam mechanism for full engagement of a leading edge of the blade body within the blade sheath.

Assignees

• United Technologies Corp

Inventors

• Parkin Michael
• Oyegun Osamuyimen A
• Rios Joseph
• Horn Thomas J
• Beckman Micah

Classifications

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• B23P15/04 Primary

  turbine or like blades from several pieces · CPC title

• F05D2230/23

  by permanently joining parts together · CPC title

• B21D53/78

  propeller blades; turbine blades · CPC title

• F01D5/147

  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 title