# US 2014/0196464 A1 · System and method for protecting components in a gas turbine engine with exhaust gas recirculation

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- Number: US 2014/0196464 A1
- Document ID: US20140196464A1
- Status: Published application
- Kind: A1
- Application number: 14/135,055
- Filed: 2013-12-19
- Published: 2014-07-17
- Earliest claimed: 2013-01-13
- Assignees: ExxonMobil Upstream Research Company; General Electric Company
- Applicants: Exxonmobil Upstream Research Company; General Electric Company
- Inventors: Pramod K. Biyani; Rajarshi Saha; Anil Kumar Dasoji; Richard A. Huntington; Franklin F. Mittricker
- Web page: https://patentgrep.com/patent/US20140196464A1

## CPC

- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F01D 25/30: Exhaust heads, chambers, or the like
- F02C 3/34: with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- Y02E 20/16: Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A system includes a gas turbine engine that includes a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The fluid supply system is configured to route an inert gas to the exhaust section.

## Claims

### Claim 1

A system, comprising:
a gas turbine engine, comprising:
a turbine section having one or more turbine stages between an upstream end and a downstream end;
an exhaust section disposed downstream from the downstream end of the turbine section; and
a fluid supply system coupled to the exhaust section, wherein the fluid supply system is configured to route an inert gas to the exhaust section.

### Claim 2 (depends on 1)

The system of claim 1, wherein the exhaust section comprises:
an exhaust passage in fluid communication with the turbine section; and
an inert gas passage coupled to the fluid supply system.

### Claim 3 (depends on 2)

The system of claim 2, wherein the inert gas passage is fluidly coupled to the exhaust passage.

### Claim 4 (depends on 3)

The system of claim 3, wherein the exhaust section comprises a wall disposed along the exhaust passage, and the inert gas passage is fluidly coupled to the exhaust passage through a plurality of openings in the wall.

### Claim 5 (depends on 2)

The system of claim 2, wherein the inert gas passage extends through at least one of an outer shroud cavity surrounding the exhaust passage, an inner shroud cavity surrounded by the exhaust passage, a vane protruding into the exhaust passage, a bearing cavity having a bearing assembly, or a combination thereof.

### Claim 6 (depends on 2)

The system of claim 2, wherein the exhaust section comprises:
an outer shroud extending circumferentially about the exhaust passage; and
a casing extending circumferentially about the outer shroud to define an outer shroud cavity, wherein the inert gas passage extends through the outer shroud cavity.

### Claim 7 (depends on 1)

The system of claim 1, wherein the gas turbine engine comprises a bearing assembly disposed within a bearing cavity of a bearing housing, and the fluid supply system is coupled to the bearing housing to route the inert gas to the bearing housing.

### Claim 8 (depends on 1)

The system of claim 1, wherein the inert gas comprises nitrogen, carbon dioxide, argon, or any combination thereof.

### Claim 9 (depends on 1)

The system of claim 1, wherein the fluid supply system is coupled to an air separation unit, a carbon capture system, a gas separator, a gas purifier, a storage tank, a pipeline, or any combination thereof.

### Claim 10 (depends on 1)

The system of claim 1, wherein the gas turbine engine comprises:
a combustor section having a turbine combustor configured to generate combustion products to drive the one or more turbine stages in the turbine section; and
a compressor section having an exhaust gas compressor driven by the turbine section, wherein the exhaust gas compressor is configured to compress and route an exhaust gas to the turbine combustor.

### Claim 11 (depends on 10)

The system of claim 10, comprising an exhaust gas extraction system coupled to the gas turbine engine, and a hydrocarbon production system coupled to the exhaust gas extraction system.

### Claim 12 (depends on 10)

The system of claim 10, wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine.

### Claim 13

A method, comprising:
combusting a fuel with an oxidant and an exhaust gas in a combustion portion of a turbine combustor to generate combustion products;
driving a turbine with the combustion products from the turbine combustor;
expanding and cooling the combustion products from the turbine through an exhaust passage in an exhaust section; and
routing an inert gas from a fluid supply system to the exhaust section.

### Claim 14 (depends on 13)

The method of claim 13, comprising routing the inert gas from the fluid supply system to an outer shroud cavity of the exhaust section, wherein the outer shroud cavity is disposed between an outer shroud and a casing of the exhaust section, and the outer shroud extends circumferentially about the exhaust passage.

### Claim 15 (depends on 13)

The method of claim 13, comprising routing the inert gas from the fluid supply system to an internal vane cavity of a vane, wherein the vane extends into the exhaust passage of the exhaust section.

### Claim 16 (depends on 13)

The method of claim 13, comprising routing the inert gas from the fluid supply system to an inner shroud cavity of the exhaust section, wherein an inner shroud extends circumferentially about the inner shroud cavity, and the exhaust passage extends circumferentially about the inner shroud.

### Claim 17 (depends on 13)

The method of claim 13, comprising routing the inert gas through a bearing cavity of the exhaust section, wherein the bearing cavity comprises a bearing assembly.

### Claim 18

A system, comprising:
a turbine exhaust section configured to mount downstream from a turbine section of a gas turbine engine, wherein the turbine exhaust section comprises an exhaust passage configured to receive exhaust from the turbine section, and an inert gas passage extending through a structure of the turbine exhaust section; and
a fluid supply system coupled to the exhaust section, wherein the fluid supply system is configured to route an inert gas to the inert gas passage in the exhaust section.

### Claim 19 (depends on 18)

The system of claim 18, wherein the inert gas passage is isolated from the exhaust passage.

### Claim 20 (depends on 18)

The system of claim 18, wherein the fluid supply system comprises a temperature control system, a pressure control system, a moisture removal system, a particulate removal system, or any combination thereof.