# US 11,028,710 B2 · Gas turbine engine component with performance feature

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- Number: US 11,028,710 B2
- Document ID: US11028710B2
- Status: Granted
- Kind: B2
- Application number: 16/155,920
- Filed: 2018-10-10
- Published: 2019-02-07
- Granted: 2021-06-08
- Earliest claimed: 2015-08-03
- Assignees: Siemens Energy, Inc.
- Applicants: Siemens Energy, Inc.
- Inventors: David G. Maire; Daniel J. Ryan; Dhafer Jouini; Ahmed Kamel; Gerald J. Bruck
- Web page: https://patentgrep.com/patent/US11028710B2

## CPC

- F01D 11/003: {by packing rings; Mechanical seals}
- B29C 73/22: the article containing elements including a sealing composition, e.g. powder being liberated when the article is damaged
- F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)}
- F01D 25/166: {Sliding contact bearing (gas bearings F01D25/22)}
- F05D 2240/55: Seals
- F05D 2260/311: of the frangible or shear type
- F05D 2260/80: Diagnostics
- F05D 2270/11: to prolong engine life
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A gas turbine engine component (50, 100, 150, 160, 174, 206, 236), including: a surface (54) subject to loss caused by a wear instrument during operation of the component in a gas turbine engine and a performance feature (80, 82, 102, 152, 162, 172, 200, 230) associated with the surface. The surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated.

## Claims

### Claim 1

A gas turbine engine component, comprising:
a surface subject to loss caused by a wear instrument during operation of the component in a gas turbine engine; and
a performance featured associated with surface;
wherein the surface and the performance feature interact in a manner that changes with the loss such that a change in performance of the gas turbine engine resulting from the loss is mitigated,
wherein before any loss the performance feature is disposed entirely below the surface subject to the loss,
wherein the performance feature comprises a flowable material that is released upon exposure and which flows onto the surface upon the exposure, wherein the gas turbine engine component comprises a seal element, wherein the wear instrument comprises a sealing surface of an adjacent component, wherein the interaction comprises physical contact between the seal element and the sealing surface, and wherein the flowable material comprises a sealant.

### Claim 2

A gas turbine engine component, comprising:
a component material subject to loss during operation caused by a wear instrument, the component material comprising a substrate surface subject to the loss;
a performance feature disposed entirely below the substrate surface subject to the loss to become exposed upon the loss,
wherein the gas turbine engine component and the wear instrument together perform a function;
wherein, before the loss, the function occurs via the substrate surface and at the substrate surface,
wherein, after the loss, the function occurs via the performance feature and at a location above the substrate surface,
wherein the performance feature comprises a sacrificial casing that sacrifices upon exposure, thereby releasing a flowable material onto the substrate surface.

### Claim 3 (depends on 2)

The gas turbine engine component of claim 2, wherein the wear instrument comprises an adjacent component, and wherein the flowable material comprises at least one of a sealant and a lubricant.

### Claim 4 (depends on 3)

The gas turbine engine component of claim 3, wherein the sacrificial casing comprises a polymer material and the flowable material comprises an epoxy sealant.