Process of boas grinding in situ

Patent metadata

Field	Value
Publication number	US-9719364-B2
Application number	US-201514613692-A
Country	US
Kind code	B2
Filing date	Feb 4, 2015
Priority date	Feb 4, 2015
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

A process for machining a turbine engine blade outer air seal in situ, the process comprising replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein the blade outer air seal is assembled in a gas turbine engine case. The process includes coupling a blower to the blade outer air seal. The blade outer air seal comprises at least one flow path. The process includes creating a purge air stream with the blower through the blade outer air seal. The process includes machining the blade outer air seal, wherein particulate is formed from the machining. The process includes preventing the particulate from blocking the at least one flow path of the blade outer air seal.

First claim

What is claimed is:

1. A process of machining air seals in situ comprising:
mounting a cutting tool assembly proximate an air seal, wherein said air seal is assembled in a gas turbine engine case;
fluidly coupling a blower to a shroud attached to said gas turbine engine case fluidly coupled to at least one cooling air passage of said gas turbine engine case;
flowing a purge air stream from said blower through said shroud through said at least one cooling air passage; and
discharging said purge air stream proximate said air seal.

2. The process according to claim 1 , wherein said purge air stream prevents particulate contamination in said gas turbine engine case.

3. The process according to claim 1 , wherein said purge air stream maintains cooling air passages of said air seal clear of particulate contamination resulting from operation of said cutting tool assembly.

4. The process according to claim 1 , further comprising coupling said blower to said cooling air passage proximate at least one of a TCA 2 nd vane supply and at least one direct diffuser exit feed area.

5. The process according to claim 1 , further comprising machining said air seal with said cutting tool assembly in situ.

6. The process according to claim 1 , wherein said air seal comprises a blade outer air seal.

7. An in situ gas turbine engine air seal machining tool assembly comprising:
an outer case;
an air seal coupled to said outer case;
at least one cooling flow path formed in said air seal;
a cutting tool assembly mounted in said gas turbine engine proximate said air seal;
a blower fluidly coupled to said case with a shroud coupled to said case, wherein said shroud is fluidly coupled to said at least one cooling flow path, said blower configured to generate a positive purge air stream flowing through said shroud to said at least one cooling flow path; and
said purge air stream configured to prevent contamination in said air seal at least one cooling flow path from particulate created by said cutting tool assembly.

8. The turbine engine component according to claim 7 , wherein said air seal comprises a blade outer air seal.

9. The assembly according to claim 8 , wherein said cutting tool assembly is configured to grind portions of said air seal.

10. The assembly according to claim 7 , wherein said blower is fluidly coupled to said at least one cooling flow path at sections of said outer case proximate at least one of a TCA 2 nd vane supply and at least one direct diffuser exit feed area.

11. The assembly according to claim 7 , wherein said at least one cooling flow path includes a first flow path, a second flow path and a third flow path of said air seal.

12. A process for machining a turbine engine blade outer air seal in situ, said process comprising:
replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein said blade outer air seal is assembled in a gas turbine engine case;
coupling a blower to said gas turbine engine case with a shroud formed over an opening in said case, said opening in said case being in fluid communication with at least one flow path formed in said blade outer air seal;
creating a purge air stream with said blower flowing downstream from said blower through said shroud and through said opening in said case through said at least one flow path and through said blade outer air seal; and
machining said blade outer air seal, wherein particulate is formed from said machining; and
preventing said particulate from blocking said at least one flow path of said blade outer air seal.

13. The process of claim 12 , wherein said blower is fluidly coupled to all sections of said gas turbine engine case.

14. The process of claim 12 , wherein said purge air stream flows through said gas turbine engine case and exits proximate said machining of said blade outer air seal.

15. The process of claim 12 , wherein said machining comprises a circumferential grind configured to minimize blade outer air seal radius variation.

Assignees

• United Technologies Corp

Inventors

• Philbrick Graham Ryan
• Couture Patrick D

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D25/12

  Cooling · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• B24B55/10

  specially designed for portable grinding machines, e.g. hand-guided · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title