# US 8,770,927 B2 · Abrasive cutter formed by thermal spray and post treatment

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- Number: US 8,770,927 B2
- Document ID: US8770927B2
- Status: Granted
- Kind: B2
- Application number: 12/911,004
- Filed: 2010-10-25
- Published: 2012-04-26
- Granted: 2014-07-08
- Earliest claimed: 2010-10-25
- Assignees: United Technologies Corporation
- Applicants: Christopher W. Strock; Changsheng Guo
- Inventors: Christopher W. Strock; Changsheng Guo
- Web page: https://patentgrep.com/patent/US8770927B2

## CPC

- F16J 15/445: {with means for adjusting the clearance}
- F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)}
- F05D 2230/13: using lasers
- F05D 2240/55: Seals
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A seal for a gas turbine engine component having an airfoil with a radial outward end and a radial inward end, one of which is bare metal. A seal member is adjacent to the bare metal end of the airfoil wherein the seal member is coated with a abrasive layer having a laser engraved surface with the top of the surface has less than about 5% of the surface area of the base of the abrasive layer.

## Claims

### Claim 1

A method of forming a seal in a rotating gas turbine engine component, the method comprising:
providing an airfoil with a radial outward end and a bare metal airfoil tip at a radial inward end;
providing a seal member adjacent to the radial inward end of the airfoil wherein the seal member is coated with an abrasive layer having a laser engraved surface comprising a grooved pattern oriented at an angle to the axis of rotation wherein the top of the grooved surface has less than about 5% of the surface area of the base of the abrasive layer.

### Claim 2 (depends on 1)

The method of claim 1, wherein the component is a compressor stator vane and the seal member includes a rotor seal surface.

### Claim 3 (depends on 1)

The method of claim 1, wherein the component is a compressor rotor blade and the seal member includes a vane seal surface.

### Claim 4 (depends on 1)

The method of claim 1, wherein the abrasive layer has a thickness ranging from about 10 mils to about 19 mils (about 254 to about 483 microns).

### Claim 5 (depends on 1)

The method of claim 1, wherein the abrasive layer has a hardness of at least 7 on the Mohs scale of mineral hardness.

### Claim 6 (depends on 5)

The method of claim 5, wherein the abrasive layer is selected from the group consisting of quartz, cubic zirconia, corundum and diamond.

### Claim 7

A gas turbine engine comprising:
an engine casing extending circumferentially about an engine centerline axis; and
a compressor section, a combustor section, and a turbine section within said engine casing containing rotating components;
wherein at least one of said compressor section and said turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil, wherein a tip of the at least one airfoil is bare metal and the at least one seal member is coated with an abrasive layer having a laser engraved surface comprising a grooved pattern oriented at an angle to the axis of rotation wherein the top of the grooved surface has less than about 5% of the surface area of the base of the abrasive layer.

### Claim 8 (depends on 7)

The engine of claim 7, wherein the airfoil is a compressor stator vane and the seal member includes a rotor seal surface.

### Claim 9 (depends on 7)

The engine of claim 7, wherein the airfoil is a compressor rotor blade and the seal member includes a casing or shroud seal surface.

### Claim 10 (depends on 7)

The engine of claim 7, wherein the abrasive layer has a thickness ranging from about 10 mils to about 19 mils (about 254 to about 483 microns).

### Claim 11 (depends on 7)

The engine of claim 7, wherein the abrasive layer has a hardness of at least 7 on the Mohs scale of mineral hardness.

### Claim 12 (depends on 11)

The engine of claim 11, wherein the ceramic layer is selected from the group consisting of quartz, cubic zirconia, corundum and diamond.

### Claim 13

A gas turbine engine component comprising:
an airfoil with a radial outward end and a radial inward end;
a seal member adjacent to the radial inward end of the airfoil wherein the seal member is coated with a abrasive layer having a laser engraved surface comprising a grooved pattern oriented at an angle to an axial direction wherein the top of the grooved surface has less than about 5% of the surface area of the base of the abrasive layer.

### Claim 14 (depends on 13)

The component of claim 13, wherein the airfoil is a compressor stator vane and the seal member includes a rotor seal surface.

### Claim 15 (depends on 13)

The component of claim 13, wherein the airfoil is a rotating compressor rotor blade and the seal member includes a casing or shroud seal surface.

### Claim 16 (depends on 13)

The component of claim 13, wherein the abrasive layer has a thickness ranging from about 10 mils to about 19 mils (about 254 to about 483 microns) and wherein the ceramic layer has a hardness of at least 7 on the Mohs scale of mineral hardness.

### Claim 17 (depends on 11)

The component of claim 11, wherein the abrasive layer is selected from the group consisting of quartz, cubic zirconia, corundum and diamond.