Vane tip machining fixture assembly

Patent metadata

Field	Value
Publication number	US-10018061-B2
Application number	US-201414774050-A
Country	US
Kind code	B2
Filing date	Mar 11, 2014
Priority date	Mar 12, 2013
Publication date	Jul 10, 2018
Grant date	Jul 10, 2018

Abstract

A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.

First claim

What is claimed is:

1. An airfoil tip machining fixture assembly, comprising:
a fixture;
a first clamp ring mountable to the fixture with a first multiple of fasteners, the first clamp ring includes a rigid back ring mounted to a resilient ring; and
a second clamp ring mountable to the first clamp ring with a second multiple of fasteners,
wherein the first multiple of fasteners are angled with respect to an engine central longitudinal axis.

2. The assembly as recited in claim 1 , wherein the resilient ring is manufactured of rubber.

3. The assembly as recited in claim 1 , wherein the resilient ring is mountable toward the fixture.

4. The assembly as recited in claim 1 , wherein the second multiple of fasteners are angled with respect to the engine central longitudinal axis.

5. The assembly as recited in claim 4 , further comprising a third clamp ring mountable to the second clamp ring with a third multiple of fasteners.

6. The assembly as recited in claim 5 , wherein the third multiple of fasteners are angled with respect to the engine central longitudinal axis.

7. A method of machining tips of a multiple of cantilevered mounted stator vane airfoils of a gas turbine engine comprising:
resiliently biasing the multiple of cantilevered mounted stator vane airfoils with a first clamp ring;
fastening the first clamp ring to a fixture with a first multiple of fasteners, the first multiple of fasteners angled with respect to an engine central longitudinal axis; and
fastening a second clamp ring to the first clamp ring.

8. The method as recited in claim 7 , further comprising:
fastening the second clamp ring to the first clamp ring with a second multiple of fasteners, the second multiple of fasteners angled with respect to the engine central longitudinal axis.

9. The method as recited in claim 7 , further comprising:
machining the tips of the multiple of cantilevered mounted stator vane airfoils with respect to the engine central longitudinal axis.

10. The method as recited in claim 7 , further comprising:
resiliently biasing the multiple of cantilevered mounted stator vane airfoils in each of a multiple of stages with a respective clamp ring.

11. The method as recited in claim 7 , further comprising:
resiliently biasing the multiple of cantilevered mounted stator vane airfoils in each of a multiple of stages with a respective clamp ring, a resilient ring of the respective clamp ring directed toward the fixture.

Assignees

• United Technologies Corp

Inventors

• Richardson Carl S
• Szymbor John A

Classifications

• B23C2215/44

  Turbine blades · CPC title

• B23C2215/045

  Propellers · CPC title

• Y10T29/4932

  Turbomachine making · CPC title

• B23C3/18

  for shaping screw-propellers, turbine blades, or impellers · CPC title

• Y10T409/30868

  Work support · CPC title