US5355668A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Catalyst-bearing component of gas turbine engine
Assignee: General Electric Co
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Filing: 1993-01-29
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Granted: 1994-10-18
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Expires: 2013-01-29
Abstract
Abstract A catalyst-bearing component of a gas turbine engine is provided. Catalytic materials are provided on components defining the gas flow path of the engine, so that emissions of carbon monoxide and unburned hydrocarbons are reduced. The catalytic materials are selected from the group consisting of noble metals and transition metal oxides. The portions of the gas flow path where such materials are advantageously applied include the combustor, the turbine and the exhaust system. The catalytic coating is preferably applied in conjunction with a thermal barrier coating system interposed between a substrate component and the catalytic coating.
Inventors
- 👤 Antoinette E. Weil
- 👤 Jon C. Schaeffer
- 👤 Julia A. Fields
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 08:52
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/28; F01D5/288; F01D25/00; F01D25/30; F23; F23R; F23R3/00; F23R3/40; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
138 words
An axial flow gas turbine engine having a compressor portion, a combustor portion, a turbine portion and an exhaust portion, in which fuel is solely supplied to a combustor portion of the engine where it is ignited to form a hot gas, the ignited gas passing through at least one turbine stage intermediate between the combustor portion and the exhaust portion, the improvement comprising: a component having a surface thereof that defines at least a portion of a gas flow path in the engine downstream from the combustor portion through the exhaust portion; and a catalytic coating, applied to at least a sufficient portion of the surface, that catalyzes the combustion of gas turbine engine fuels to reduce emission of unburned hydrocarbons and carbon monoxide by at least 15% at a fuel to air equivalence ratio of 0.8.
Claim 2
Dependent Claim
138 words
An axial flow gas turbine engine having a compressor portion, a combustor portion, a turbine portion and an exhaust portion, in which fuel is solely supplied to a combustor portion of the engine where it is ignited to form a hot gas, the ignited gas passing through at least one turbine stage intermediate between the combustor portion and the exhaust portion, the improvement comprising: a component having a surface thereof that defines at least a portion of a gas flow path in the engine downstream from the combustor portion through the exhaust portion; and a catalytic coating, applied to at least a sufficient portion of the surface, that catalyzes the combustion of gas turbine engine fuels to reduce emission of unburned hydrocarbons and carbon monoxide by at least 15% at a fuel to air equivalence ratio of 0.8.
Claim 3
Dependent Claim
19 words
The component of claim 1, wherein the component is a part of a turbine of the gas turbine engine.
Claim 4
Dependent Claim
20 words
The component of claim 1, wherein the component is a part of an exhaust system of the gas turbine engine.
Claim 5
Dependent Claim
26 words
The component of claim 1, wherein the catalytic coating is comprised of a material selected from the group consisting of noble metals and transition metal oxides.
Claim 6
Dependent Claim
13 words
The component of claim 1, wherein the component is comprised of a superalloy.
Claim 7
Dependent Claim
49 words
The component of claim 1, wherein the component is comprised of a superalloy material coated with a ceramic thermal barrier coating, and wherein the catalytic coating is applied to the thermal barrier coating so that the thermal barrier coating is interposed between the catalytic coating and the superalloy material.
Claim 8
Dependent Claim
27 words
The component of claim 6, wherein the thermal barrier coating system includes a layer of yttria-stabilized zirconia which contains between 8 and 20 percent yttria by weight.
Claim 9
Dependent Claim
19 words
The component of claim 6, wherein the component is a part of a turbine of the gas turbine engine.
Claim 10
Dependent Claim
20 words
The component of claim 6, wherein the component is a part of an exhaust system of the gas turbine engine.
Claim 11
Dependent Claim
14 words
The component of claim 1, wherein the component is comprised of a ceramic material.
Claim 12
Dependent Claim
35 words
The method of claim 8 wherein the material that catalyzes combustion is applied to the portion of the flow path surface by a process selected from the group consisting of thermal spray and vapor deposition.
Claim 13
Dependent Claim
23 words
The component of claim 1, wherein the surface roughness of the catalytic coating is between about 100 and about 250 microinches arithmetic average.
Claim 14
Dependent Claim
23 words
The component of claim 4 wherein the catalytic coating has a density between about 70 and about 90 percent of its theoretical density.
Claim 15
Independent Claim
136 words
A method for reducing emissions of unburned hydrocarbons and carbon monoxide from an axial gas turbine engine which includes a compressor portion, a combustor portion, a turbine portion and an exhaust portion, in which fuel is solely supplied to a combustor portion of the engine where it is ignited to form a hot gas, the ignited gas passing through at least one turbine stage intermediate between the combustor portion and the exhaust portion and having a flow path surface from the combustor portion downstream through the exhaust portion, the method comprising fabrication of at least a sufficient portion of the flow path surface with a material that catalyzes combustion of gas turbine engine fuels to reduce emission of unburned hydrocarbons and carbon monoxide by at least 15% at a fuel to air equivalence ratio of 0.8.
Claim 16
Independent Claim
136 words
A method for reducing emissions of unburned hydrocarbons and carbon monoxide from an axial gas turbine engine which includes a compressor portion, a combustor portion, a turbine portion and an exhaust portion, in which fuel is solely supplied to a combustor portion of the engine where it is ignited to form a hot gas, the ignited gas passing through at least one turbine stage intermediate between the combustor portion and the exhaust portion and having a flow path surface from the combustor portion downstream through the exhaust portion, the method comprising fabrication of at least a sufficient portion of the flow path surface with a material that catalyzes combustion of gas turbine engine fuels to reduce emission of unburned hydrocarbons and carbon monoxide by at least 15% at a fuel to air equivalence ratio of 0.8.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-10-17 | 1998-04-18 | 1998-10-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-10-17 | 2002-04-18 | 2002-10-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-10-17 | 2006-04-18 | 2006-10-18 | $7700.00 | Window Closed / Lapsed |