Ceramic matrix composite rotor blade attachment and method of manufacture therefor

Patent metadata

Field	Value
Publication number	US-11143040-B2
Application number	US-201916590925-A
Country	US
Kind code	B2
Filing date	Oct 2, 2019
Priority date	Oct 2, 2019
Publication date	Oct 12, 2021
Grant date	Oct 12, 2021

Abstract

A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y′ and Z′ axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y′ and Z′ axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y″ and Z″ axis datum with respect to the Y′ and Z′ axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y″ and Z″ axis datum; and machining off the sacrificial datum system removing the V-notches.

First claim

What is claimed:

1. A component with an airfoil for a gas turbine engine, comprising:
an airfoil;
a composite root with a multiple of outer composite plys, the composite root extends from the airfoil; and
a machined coating layer at least partially around the composite root, the final machined layer machined from an oversized coating layer, wherein none of the outer composite plys under the machined coating layer applied as the oversized coating layer prior to being machined to form the machined coating layer are cut during machining of the oversized coating layer, the oversized coating layer having had machined V-notches that form a Y′ and Z′ axis datum of a sacrificial datum in relation to a primary Y and Z axis datum prior to being machined to form the machined coating layer.

2. The component as recited in claim 1 , wherein the oversized coating layer prior to being machined is of a thickness between 0.030-0.040 inch (0.762-1.016 mm).

3. The component as recited in claim 2 , wherein the machined coating layer is of a thickness of 0.010 inches (0.254 mm).

4. The component as recited in claim 2 , wherein the machined coating layer fills the plys of the root to provide a smooth final interface surface.

5. The component as recited in claim 2 , wherein the machined coating layer extends to an underplatform region of ceramic matrix composite blade that extends to the composite root.

6. The component as recited in claim 1 , wherein the component is a rotor blade.

7. The component as recited in claim 1 , wherein the outer composite plys follow an outer mold line.

8. The component as recited in claim 7 , wherein a relative position of the outer composite plys are positioned within tolerances that are less than +/−0.005 inch (+/−0.127 mm).

9. The component as recited in claim 7 , wherein the outer composite plys form a smooth ply transition at an attachment fillet radii.

10. The component as recited in claim 7 , wherein the attachment fillet radii define an interface with a respective blade slot in a rim of the disk.

11. A process for manufacturing a composite component, comprising:
manufacturing an oversized root region of a composite component;
fixturing the composite component into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the oversized root region;
machining V-notches into the oversized root region to form a Y′ and Z′ axis datum of a sacrificial datum in relation to the primary Y and Z axis datum;
applying an oversized coating layer over the attachment fillet radii of the root region;
fixturing the composite component into a machining fixture at the Y′ and Z′ axis datum of the sacrificial datum;
machining the oversized coating layer to a machined coating layer forming a Y″ and Z″ axis datum with respect to the Y′ and Z′ axis datum of the sacrificial datum;
fixturing the composite component into a machining fixture at the Y″ and Z″ axis datum; and
machining off the sacrificial datum removing the V-notches.

12. The process as recited in claim 11 , wherein machining the oversized coating layer to the machined coating layer avoids cutting any of a multiple of outer composite plys that form the attachment fillet radii of the root region.

13. The process as recited in claim 12 , wherein a relative position of the outer composite plys are positioned within tolerances that are less than +/−0.005 inch (+/−0.127 mm).

14. The process as recited in claim 13 , wherein the outer composite plys are outer plys which follow an outer mold line contour to create a smooth ply transition at the attachment fillet radii.

15. The process as recited in claim 14 , wherein the attachment fillet radii define an interface with a respective blade slot in a rim of the disk.

16. The process as recited in claim 11 , further comprising machining an undercut and a clearance cut into the oversized root region to at least partially form a root profile of the root region prior to applying the oversized coating layer.

17. The process as recited in claim 11 , further comprising silicon plasma spraying the oversized coating layer.

18. The process as recited in claim 11 , further comprising additively manufacturing the oversized coating layer.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Mccaffrey Michael G
• Mentz Karl A
• King Christopher
• Doll Stephen D
• Ledbetter Aurelia

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F01D5/282 Primary

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

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title